Vol 4 No 1
January 2001
Ground Testing Technical Committee
Chairman’s Message
Welcome to the newest edition of the newsletter of the
American Institute of Aeronautics and Astronautics
(AIAA) Ground Testing Technical Committee (GTTC). You
will find that this publication, like the GTTC itself, is about
taking action and getting involved, furthering the AIAA
technical agenda, and making the most of AIAA
contributions. The GTTC is dedicated to the advancement
of ground testing in support of the aerospace sciences.
The committee strives to be innovative in its approach
and to continuously look for new areas to explore. Our
membership represents the full spectrum of aerospace
ground testing expertise and we pride ourselves on our
ability to be open to new ideas. We rely on guidance
from our members and from you to help us select the
most relevant ground test topics for special consideration.
Our main subcommittees are in the technical areas of
aerodynamics and propulsion. Through an innovative
working group structure, most of the technical work we
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Outstanding Papers
3
Membership
4
Subcommittee News
6
Working Groups
8
Student Contest
9
Congressional Visits Day
10
Ground Testing News
17
Special Topics
18
Committee News
19
GTTC Calendar
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Membership Information
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do incorporates participation from outside of the GTTC
membership. The subcommittees and working groups
are active in six areas of study, completing products and/
or documents in the areas of
• Experimental uncertainty
• Internal balance technology
• Wind tunnel calibration methodology
• Test processes
• Thrust stands
• Flow quality
To improve communication and to support a proactive
approach to solving common problems, the GTTC
maintains numerous liaisons throughout the AIAA and
industry.
The GTTC has made strides in improving the quality of
our conference sessions with technical programs that
focus on current ground testing problems and solutions.
We have also been busy with numerous other activities
to support our goals. These include the continuation of
our Student Design Competition to recognize and
encourage the work of AIAA’s collegiate members, the
selection of Outstanding Papers from technical papers
presented at last summer’s Advanced Measurement
Technology and Ground Testing Conference (AMT/GT)
(see announcement in this newsletter), the presentation
of our National Ground Testing Award, and participation
in the planning and execution of AIAA’s annual
Congressional Visits Day.
The GTTC provides a forum for its diverse membership
to discuss new issues and ideas. The committee comprises
a skills blend of 35 AIAA professionals from commercial,
government, and academic sectors involved in ground
testing of aerodynamics and propulsion systems. We
benefit from the enthusiasm of members who are always
seeking new opportunities and challenges. Through our
associate membership and international programs, we
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Continued from pg 1
also encourage young professionals (under age 35) to
participate, as well as those who work outside the United
States.
Since we are always looking to increase our value to AIAA
members and the aerospace community, I invite you to
send comments or suggestions regarding any of our
activities directly to me:
Dan.Marren@arnold.af.mil
If you wish to learn more about our technical activities, get
involved as a member, or join an active and dynamic
technical committee, you may visit our web site
[www.lions.odu.edu/~dlandman/gttchome.html] or
contact the committee chairman, Dan Marren, at 301–394–
1750 or chairman-elect, Allen Arrington, at 216–433–8551.
Outstanding Ground Testing Papers from the
21st AMT/GT Conference
The GTTC is pleased to announce the selection of three
Outstanding Papers from the 21st AMT/GT Conference in
Denver in June 2000. Five papers were submitted by the
various session chairpersons for consideration. A review
committee of five GTTC members ranked the papers. Three
papers were selected as outstanding:
“Langley Wind Tunnel Data Quality Assurance—Check
Standard Results” (AIAA-2000-2201).
Michael J. Hemsch, NASA Langley Research Center; John P.
Grubb and William B. Krieger, Lockheed Martin Technology
Services Group; and Daniel L. Cler, NASA Langley Research
Center.
2000-2521).
Jonathan W. Naughton, University of Wyoming; and Mark
Sheplak, University of Florida.
We extend our congratulations to each of these authors
who have made a significant contribution to the conference,
the ground testing community, the AIAA, and the aerospace
industry.
The GTTC selects papers from each of its conferences to
recognize important work in the field of aerospace ground
testing that demonstrates outstanding research,
documentation, and presentation. These three exceptional
papers were selected after a rigorous review process from
all papers presented in GTTC sessions at the AMT/GT. The
primary criteria are technical quality and relevance to
aerospace systems ground testing. Chosen papers are
recommended for publication in the appropriate AIAA
journals and the authors are presented with a certificate
and a letter to their management announcing their
achievement.
Related Links
The networking that we do to share ideas and information
within the ground test community is vital to our success.
This newsletter is just one way that the GTTC aids the
community by providing updates on ground testing current
events.
There are a lot of other great sources of information on
aerospace and ground testing news. Mike Worthey
produces a fairly new newsletter called The Wind Tunnel
Connection, together with a web site:
http://www.worthey.net/windtunnels/
“Numerical and Experimental Investigation of CO 2
Condensate Behavior in Hypersonic Flow” (AIAA-20002379).
P.J. Erbland and D.P. Rizzetta, Air Vehicles Directorate, Air
Force Research Laboratory, Wright-Patterson Air Force Base;
and R.B. Miles, Department of Mechanical and Aerospace
Engineering, Princeton University.
“Modern Skin Friction Measurement Techniques:
Description, Use, and What To Do With the Data” (AIAA-
This web site was established to provide useful information
to aerospace professionals and engineers engaged in the
design, testing, and fabrication of aerospace vehicles,
hardware, and software. The newsletter provides updates
on wind tunnel activities at various sites around the world
(you can request the newsletter through the web site listed
above, or visit GTTC (http://www.aero.odu.edu/
~dlandman/gttchome.html) and look for the Wind Tunnel
Connection under “Links”).
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Vol 4 No 1
January 2001
AIAA / GTTC 2001 Membership
Technical Working Groups
2001 GTTC Officers
Chairman
Daniel E. Marren
301–394–1750
Aerodynamics Subcommittee
Nancy Swinford
408–743–1443
Publications Subcommittee
David Minto
505–679–2133
Test Processes
Mark R. Melanson
817–763–1760
Vice Chairman
E. Allen Arrington
216–433–8507
Propulsion Subcommittee
Susan T. Hudson
662–325–6602
Standards Subcommittee
Susan T. Hudson
662–325–6602
Flow Quality Working Group
Frank W. Steinle, Jr.
931–454–7716
Secretary
Nancy Swinford
408–743–1443
Awards Subcommittee
L. Brent Bates
931–454–4943
Steering Committee
Daniel E. Marren
301–394–1750
Internal Balances
David M. Cahill
931–454–6725
Conferences Subcommittee
Frank K. Lu
817–272–2603
Student Activities Subcommittee
Bonnie L. Johnson
316–978–3569
Wind Tunnel Calibrations
E. Allen Arrington
216–433–8507
Thrust Stands
Daniel Cresci
516–737–6100 ext. 109
Membership Subcommittee
E. Allen Arrington
216–433–8507
Gregory Addington
Thomas Aiken
Dr. Stephen A. Arnette
E. Allen Arrington
L. Brent Bates
Dr. Thomas J. Beutner
Jean Bianco
Richard Burrows
David M. Cahill
Julie Carlile
Stephen Craft
Daniel Cresci
Mark Cross
Jeffery Emdee
Eric Ernst
Thomas Fetterhoff
John Hayes
Dennis W. Hergert
Dr. Susan T. Hudson
Dr. Bonnie L. Johnson
Dr. Jerry Kegelman
Jeffrey Kirk
Ray Knowis
Dr. Drew Landman
Dr. Jan Lepicovsky
Dr. Frank K. Lu
Dr. John Magill
Daniel E. Marren
Dr. Thomas McLaughlin
Mark R. Melanson
David Minto
James Norton
Mark L. Perry
Dr. Mark Rennie
Mathew L. Rueger
Dr. Frank W. Steinle, Jr.
Samuel Stephens
Todd Sterk
William A. Straka
Nancy Swinford
Niek Verhaagen
Air Force Research Laboratory/VACA
NASA Ames Research Center
Manager, Aeronautics Engineering Research/Sverdrup Technology, Inc.
Supervisor, Mechanical Operations/Dynacs Engineering
Sr. Engineer/Sverdrup Technology, Inc. (AEDC)
Program Manager/Air Force Office of Scientific Research
PSL Facility Manager/NASA Glenn Research Center
Sr. Engineering Specialist/Boeing
Engineering Specialist/Sverdrup Technology, Inc. (AEDC)
Air Force Research Laboratory
NASA Langley Research Center
Sr. Scientist/GASL, Inc.
Sverdrup Technology, Inc.
The Aerospace Corporation
Cryogenics Testbed Manager/NASA Kennedy Space Center
Arnold Engineering Development Center (AEDC)/XPV
Pratt & Whitney
Sr. Principal Engineer/Boeing Phantom Works
Ass’t. Professor/Mississippi State University, Mechanical Engineering
Director, Aerodynamic Labs/National Institute for Aviation Research
NASA Langley Research Center
Engineering Specialist/Lockheed Martin Missiles and Fire Control
Sr. Vice President/Micro Craft, Inc.
Old Dominion University
Project Manager/Dynacs Engineering
Assoc. Professor/University of Texas at Arlington
Physical Sciences Inc.
Wind Tunnel Projects Manager/White Oak (AEDC)
Aeronautics Research Consultant/U.S. Air Force Academy
Engineering Chief, Model Design/Lockheed Martin Aeronautics
Holloman High-Speed Test Track/U.S. Air Force
Director, Operations/Integrated AeroSystems
Lead Projects Engineer/Lockheed Martin
Aerodynamicist/Aiolos Engineering Corp.
Sr. Project Engineer/Boeing
Sr. Engineering Specialist/Sverdrup Technology, Inc. (AEDC)
Lockheed Martin Stennis Operations
Sandia National Laboratory
Assoc. Research Engineer/Penn State Applied Research Laboratory
Manager II PEL, Aero/Fluids Group/Lockheed Martin Space Systems
Sr. Research Scientist/Vortex Aerodynamics and Acoustics
GTTC Newsletter GTTC Newsletter GTTC Newsletter
937–255–8490
650–604–6855
931–393–6699
216–433–8507
931–454–4943
703–696–6961
216–433–8870
562–797–5651
931–454–6725
661–275–5098
757–864–4817
516–737–6100 ext. 109
931–454–5952
310–336–7704
407–867–2133
931–454–5870
561–796–4397
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662–325–6602
316–978–3569
757–864–8022
972–603–2419
615–455–2617 ext. 504
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978–689–0003
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931–454–7716
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505–844–4923
814–863–3009
408–743–1443
31–15–278–6385
gregory.addington@va.afrl.af.mil
taiken@mail.arc.nasa.gov
arnettsa@sverdrup.com
earnest.a.arrington@grc.nasa.gov
brent.bates@arnold.af.mil
tom.beutner@afosr.af.mil
jean.bianco@grc.nasa.gov
richard.burrows@west.boeing.com
david.cahill@arnold.af.mil
julie.carlile@ple.af.mil
s.j.craft@larc.nasa.gov
dcresci@gasl-usa.com
mark.cross@arnold.af.mil
jeffery.l.emdee@aero.org
eric.ernst-1@ksc.nasa.gov
thomas.fetterhoff@arnold.af.mil
hayesjoh@pwfl.com
dennis.w.hergert@boeing.com
hudson@me.msstate.edu
bjohnson@wsuhub.uc.twsu.edu
j.t.kegelman@larc.nasa.gov
jeffrey.kirk@lmco.com
rknowis@microcraft.com
dlandman@.odu.edu
jan.lepicovsky@grc.nasa.gov
lu@mae.uta.edu
magill@psicorp.com
dan.marren@arnold.af.mil
tom.mclaughlin@usafa.af.mil
mark.r.melanson@lmco.com
dave.minto@46tg.af.mil
jnorton.ias@dabico.com
mark.l.perry@lmco.com
mark@aiolos.com
mathew.l.rueger@boeing.com
frank.steinle@arnold.af.mil
samuel.stephens@ssc.nasa.gov
tmsterk@sandia.gov
was@wt.arl.psu.edu
nancy.swinford@lmco.com
n.g.verhaagen@lr.tudelft.nl
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January 2001
GTTC Subcommittee News
The GTTC subcommittees are the backbone of our organization and create opportunities for the GTTC members to get
involved with the workings of this AIAA Technical Committee. The GTTC is subdivided into two primary subcommittees,
Aerodynamics and Propulsion. Each GTTC member is assigned to one of these primary subcommittees.
Membership in other GTTC subcommittees depends upon the member’s interest (for the Liaison, Publications, Standards,
Student Activities, and Awards and Upgrades subcommittees) or the office held within the GTTC (for the Steering,
Conferences, and Membership subcommittees).
If you have an interest in a specific subcommittee, please feel free to attend the next meeting. GTTC subcommittee
meetings coincide with GTTC-supported conferences. Specific dates, times, and locations can be found in the conference
registration materials.
The Steering Subcommittee reviews GTTC policy, AIAA
business, and all matters of general interest to GTTC members.
The Steering Subcommittee is headed by the GTTC chair and
includes the vice chair, secretary, and all subcommittee chairs.
The success of our technical committee has been recognized
by AIAA Headquarters. The GTTC has prepared and presented
AIAA training sessions for new technical committee
chairpersons.
Daniel E. Marren
White Oak (AEDC)
1999, “Assessment of Experimental Uncertainty with
Application to Wind Tunnel Testing.” The subcommittee is
now working on a related AIAA publication, “Guide for
Assessing Experimental Uncertainty—Supplement to AIAA S071A -1999.” This document will provide additional
information and examples to assist the experimenter in
applying uncertainty analysis techniques and performing an
uncertainty analysis. The information contained in the
standard and this guide is not limited to wind tunnel testing
and can be applied to a wide range of experiments.
Susan T. Hudson
Mississippi State University Mechanical Engineering
Membership Subcommittee
Aerodynamics Subcommittee
The Membership Subcommittee, which comprises the vicechairs of the GTTC and of the Aerodynamics and Propulsion
subcommittees, tries to provide a balance in technical
background and represented organizations when reviewing
applications for new members. Selected new members are
notified in March. Applicants who are not selected in one
year are eligible for consideration the following year. The large
number of applications to the GTTC has created a considerable
pool of eligible representatives from all arenas of the aerospace
community.
E. Allen Arrington
Dynacs Engineering
The Aerodynamics Subcommittee promotes the advancement
of aerodynamic ground testing technology. Members of this
committee serve as liaisons to several other committees, such
as the High-Speed Civil Transport Coordination Committee,
the Thermophysics Technical Committee, the Applied
Aerodynamics Technical Committee, and the Institute for
Aerospace Research of the National Research Council of
Canada.
Nancy Swinford
Lockheed Martin
Steering Subcommittee
Conference Planning Subcommittee
The Standards Subcommittee consists of members from both
the Aerodynamics and Propulsion subcommittees. It promotes
the understanding of ground testing, the standardization of
uncertainty analysis methodology, and the widespread use
of uncertainty analysis techniques. Recently, the
subcommittee published a revision to AIAA Standard S-071A-
The Conference Planning Subcommittee, as its name implies,
plans and organizes GTTC conferences and sessions. The GTTC
sponsors a biennial ground test technical conference and also
supports two annual AIAA conferences with ground testing
sessions. Beginning in 1996, the conference has also been
supported by the AIAA Aerodynamic Measurements Technical
Committee as the Advanced Measurement Technology and
Ground Testing Conference. These conferences are typically
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GTTC Subcommittee News
colocated with other AIAA technical conferences held in the
early summer months.
The committee also plans and organizes the GTTC-sponsored
sessions for the annual Aerospace Sciences Meeting in January
and the Joint Propulsion Conference (on odd-numbered years
only). Planning and organizing activities include electing
conference chairs; selecting session chairpersons, the
conference program, and the site and meeting room; preparing
the Call for Papers; and planning of coordinated short courses,
tours, luncheons, special exhibits, and so forth.
Frank K. Lu
University of Texas at Arlington
outstanding achievement in the ground testing field. The 2000
Ground Testing Award was presented to Travis Binion
(formerly of the Arnold Engineering Development Center)
in June 2000 at the 21st AIAA Advanced Measurement
Technology and Ground Testing Conference in Denver.
The Outstanding Paper Award recognizes the technical quality,
technical relevance, presentation, and readability of papers
presented at the various GTTC sessions. Three papers from
the 21st AMT/GT Conference were given this award.
L. Brent Bates
Sverdrup Technology, Inc. (AEDC)
Publications Subcommittee
Propulsion Subcommittee
The Propulsion Subcommittee promotes the advancement of
ground testing technology related to aeropropulsion systems.
Members of this committee serve as liaisons to several other
committees such as the Propulsion Technical Committee, the
Turbine Test Facility Working Group, and the Turbine Engine
Testing Working Group.
Susan T. Hudson
Mississippi State University Mechanical Engineering
Liaisons Subcommittee
The Liaisons Subcommittee was formed to foster
communications with AIAA Headquarters, other AIAA
technical committees, and independent societies and
organizations. GTTC members are encouraged to become
liaisons to groups that share their professional interests.
Representatives of liaison organizations are invited to attend
GTTC meetings and exchange information with members to
our mutual benefit. These exchanges may include sharing of
administrative methods, participation in joint endeavors and
innovative projects, or information about conferences and
technical programs. Liaison reports are summarized in a
standard format and published as addenda to the GTTC
minutes.
Daniel E. Marren
White Oak (AEDC)
Awards and Upgrades Subcommittee
The Awards and Upgrades Subcommittee coordinates and
participates in the selection process for the annual Ground
Testing Award presented by AIAA. This award is presented for
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The Publications Subcommittee promotes the efforts of the
various GTTC subcommittees through dissemination and
publication of technical information, journal articles, and use
of other forms of media.
In addition to the annual Aerospace America Highlights article,
the committee is responsible for preparing and publishing
the GTTC Newsletter and maintaining the technical
committee’s web site. Ground testing-related articles and
news items for use in Aerospace America Highlights and the
GTTC Newsletter are solicited from current and former GTTC
members and others in the ground testing community.
David Minto
Holloman High-Speed Test Track/U.S. Air Force
Student Activities Subcommittee
The Student Activities Subcommittee coordinates a GTTC
Engineering Contest each year for undergraduate and graduate
students. The winners receive honoraria for their efforts, as
well as the chance to attend an AIAA professional conference
through a financial donation by Pratt & Whitney. Encourage
students at your area universities to submit their projects by
handing out the flyer included in this newsletter to your
sections, and please volunteer to judge the projects after they
have been submitted.
The subcommittee also encourages interaction between GTTC
members and their local schools. New ideas for experiments
and/or testing kits for students who want to learn about flight
and aviation are always needed. Please send your ideas to Drew
Landman, along with any interesting web links on sciencerelated activities you may encounter.
Bonnie L. Johnson
National Institute for Aviation Research
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Vol 4 No 1
January 2001
GTTC Working Group News
Five Working Groups are currently operating in the GTTC. The working groups and chairmen are Internal Balance
Technology, David M. Cahill; Test Processes, Mark R. Melanson; Wind Tunnel Calibration Methodology, E. Allen
Arrington; Thrust Stands, Daniel Cresci; and Flow Quality, Frank W. Steinle, Jr. Recent working group progress is
presented below.
Wind Tunnel Calibration Methodology Working Group
E. Allen Arrington, chair
The Wind Tunnel Calibration Methodology Working Group held its 10th series of meetings in June 2000 as part of
the Advanced Measurement Technology and Ground Testing Conference in Denver. At present, the 16 members are
completing the first draft of a best-practices guide on wind tunnel calibration. During the June meeting, it was
decided to include case studies on actual tunnel calibration programs in the guide to better illustrate how tunnel
calibrations are conducted. Assignments for the remaining guide sections were also made. The current plan is to
complete the draft for the January 2001 meeting in Reno.
The Wind Tunnel Calibration Methodology Working Group was formed in 1996 to provide a forum for the exchange
of ideas and information about wind tunnel calibration. Since so many topics are relevant to wind tunnel calibration,
the initial scope of the working group was limited to the empty test section calibration of subsonic and transonic
wind tunnels.
Each member of the working group has made valuable contributions to the success of the group. The current
membership is provided below:
Dr. Steven A. Arnette
Allen Arrington (chair)
Dr. Thomas J. Beutner
Alan Boone
Colin Britcher
Andy Garrell
Jim Hallissy
Dennis W. Hergert
Dr. Bonnie L. Johnson
Mark Kammeyer
Mike Mills
Mark L. Perry (vice-chair)
Dr. Mark Rennie
David Sanford
Lew Scherer
Dr. Frank W. Steinle, Jr.
Jim Thain
Sverdrup Technology, Inc.
Dynacs Engineering, NASA Glenn Research Center
Air Force Office of Scientific Research
NASA Ames Research Center
Old Dominion University
Veridian Engineering
NASA Langley Research Center
Boeing Phantom Works
National Institute for Aviation Research
Boeing (St. Louis)
Sverdrup Technology, Inc. (AEDC)
Lockheed Martin
Aiolos Engineering Corp.
Micro Craft, Inc.
Northrop Grumman
Sverdrup Technology, Inc. (AEDC)
NCR/IAR
arnettsa@sverdrup.com
earnest.a.arrington@grc.nasa.gov
tom.beutner@afosr.af.mil
aboone@mail.arc.nasa.gov
britcher@aero.odu.edu
garrell@calspan.com
j.b.hallissy@larc.nasa.gov
dennis.w.hergert@boeing.com
bjohnson@wsuhub.uc.twsu.edu
mark.e.kammeyer@boeing.com
millsml@hap.arnold.af.mil
mark.l.perry@lmco.com
mark@aiolos.com
dsanford@microcraft.com
scherle@mail.northgrum.com
steinle.frank@hap.arnold.af.mil
jim.thain@nrc.ca
Thrust Stand Working Group
Daniel Cresci, chair
The Thrust Stand Working Group has been inactive as of late, but steps are being taken to start things moving again.
The group could always use additional participation in tackling this common issue. Please contact Chair Daniel
Cresci at 516–737–6100, ext. 109, or at dcresci@gasl-usa.com for additional information.
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Test Processes Working Group
Mark R. Melanson, chair
The Test Processes Working Group was formed in late 1992 to address concerns from wind tunnel model manufacturers
that the industry was not bringing model manufacturing companies onboard early in test development. Various
representatives sought out the AIAA as a forum to discuss and develop effective partnering methods between users
and producers of wind tunnel test articles.
After 2 years of discussion, the group focused on providing recommended practices for wind tunnel testing as a
whole. While the original concept for the working group had merit, separating the design and fabrication of test
articles from the whole process of wind tunnel test development was not practical, and a broader goal was defined.
A two-part document was envisioned: the first part aimed at aircraft (or other aeronautic) program managers to set
overall test program direction, and the second aimed at those charged with the actual execution of tests. The twopart document was begun in early 1995. Throughout each document, key activities and lessons learned would be
described to help produce successful test programs and projects.
Both parts of the document are complete and in final edit with a projected final review and publication in mid-2001.
All participants of the working group have enjoyed the interaction necessary to achieve this goal and have invested
tremendous skill and ability into the final consensus document.
At the time of this publication, members of the working group include
Thomas Aiken
E. Allen Arrington
Chris Athaide
Jean Bianco
Julie Carlile
Drew Hope
Ray Knowis
Daniel E. Marren
Laura McGill
Mark R. Melanson
Lew Scherer
Rob Sheehan
Dr. Frank W. Steinle, Jr.
William A. Straka
Steven Westmore
NASA Ames Research Center
Dynacs Engineering, NASA Glenn Research Center
Tri Models Inc.
NASA Glenn Research Center
Air Force Research Laboratory
NASA Langley Research Center
Micro Craft, Inc. (retired)
White Oak (AEDC)
Raytheon
Lockheed Martin (chair)
Northrop Grumman
Northrop Grumman
Sverdrup Technology, Inc. (AEDC)
Penn State Applied Research Laboratory
Boeing Phantom Works
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taiken@mail.arc.nasa.gov
earnest.a.arrington@grc.nasa.gov
cathaide@trimodels.com
jean.bianco@grc.nasa.gov
julie.carlile@ple.af.mil
d.j.hope@larc.nasa.gov
rknowis@microcraft.com
dan.marren@arnold.af.mil
ljmcgill@west.raytheon.com
mark.r.melanson@lmco.com
scherle@mail.northgrum.com
sheehro@mail.northgrum.com
frank.steinle@arnold.af.mil
was@wt.arl.psu.edu
steven.westmore@PSS.Boeing.com
www.lions.odu.edu/~dlandman/gttchome.html
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January 2001
GTTC Student Contest
2001 AIAA Ground Test Technical Committee
Student Engineering Contest
First Place:
$1000 plus up to $1000 travel to the AIAA Ground Test Conference
Second Place:
$500
Important Deadlines:
16 March 2001 Abstracts Due
4 May 2001
Final Reports Due
The AIAA Ground Testing Technical Committee, working in conjunction with the AIAA Student Programs Office and
numerous aerospace companies, is pleased to offer an aerospace engineering contest to graduate and undergraduate
students in aerospace, aeronautical, and related engineering academic programs. The purpose of this contest is to
provide an opportunity for interested engineering students to broaden their learning and understanding of the role
of ground testing in their aerospace discipline. The winners will be invited to attend and participate in an AIAA
professional conference.
The contest is open to all junior and senior undergraduate and all graduate students in an engineering program
accredited by the Accreditation Board for Engineering and Technology (ABET) or an equivalent engineering program
offered by a degree-granting institution recognized by the AIAA. Participants must have continuous enrollment in
their program of study throughout the contest period, August 2000 through May 2001. Teams of one to six qualified
students can submit a project. Projects can be an extramural project, part of a design or special projects course, or
part or all of a graduate thesis. It is essential that the work reported be primarily the work of the student (team) and
that the contributions of others outside the team be clearly indicated.
To enter, submit an abstract, 500 words or less, detailing the Problem Description, Project Relevance, Research Approach,
and Potential Outcome. Include a cover letter containing the level for each student (junior, senior, M.S. or Ph.D.),
mailing address, telephone number and facsimile number, signature of each student (team) member, and signature
of the faculty advisor of the project. Also include a signed statement by the AIAA faculty advisor stating that the
project meets the requirements set forth herein.
A team of engineers and scientists from industry, government, and academia will evaluate the abstracts and final
reports.
Final project submission details will be mailed upon receipt of the abstract. Mail abstracts to
Bonnie L. Johnson, Director of Aerodynamic Labs
Wichita State University/National Institute for Aviation Research
1845 North Fairmount
Wichita, KS 67260–0093
Voice: 316–978–3569, facsimile: 316–978–3521
E-mail: bjohnson@twsu.edu
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GTTC Congressional Visits Day 2000
GTTC Members Participate in Congressional Visits Day 2000
Several Ground Test Technical Committee members had the opportunity to participate in the 2000
“Congressional Visits Day” or CVD event, which was the largest to date. Tom Beutner and Mark Melanson
represented the technical committee and were among approximately 200 participants.
The message conveyed to Congress was that the Federal Government must make a long-term commitment to
aerospace research and development (R&D). Aeronautics and astronautics R&D has made major contributions
to America’s prosperity and the quality of life of the general public. In addition, an attempt was made to
define the appropriate role of the Federal Government in supporting aerospace R&D.
The program began with an orientation that included briefings on the CVD 2000 message, “The Do’s and Don’ts
on Capitol Hill,” and was followed by a welcoming reception at the Washington Court Hotel, which allowed
participants and AIAA staff the opportunity to discuss the next day’s activities. AIAA members Carol Cash
(aeronautics), Phil Hattis (astronautics), and Cecil Black (defense) presented FY 2001 budget overviews.
Other key speakers throughout the two days included Congressman David Weldon (R-FL), who talked about
aerospace, Congressman Herb Bateman (R-VA), who spoke about aeronautics, and former CIA Director Jim
Woolsey, who discussed defense issues.
For the Congressional visits, AIAA staff established teams and meeting schedules in advance to maximize
coverage and match AIAA representatives with Congressional Representatives or Senators from their own district
or state, when possible. The teams fanned out to the Capitol to talk with key members of Congress and their
staffs about the AIAA message, and to leave behind short writeups on the message provided by AIAA. Several
teams also had the opportunity to attend hearings on key aerospace or research issues.
Congressional Visits Day 2000 concluded with a Congressional Reception in the Rayburn House Office Building
on Capitol Hill that allowed AIAA participants, Members of Congress, and Hill staffers to network with one
another.
Most participants were favorably impressed by the 2-day event. As a first-time participant, Mark Melanson
commented, “I expected the level of knowledge about the message to be low, but I was amazed at just how
tuned-in the members of Congress and their staffs are to this issue. The other thing that impressed me was
that most of the staff are very young—not many are over 30.” Tom Beutner added, “AIAA did a great job of
scheduling meetings and putting this event together. The invited speakers were outstanding, and I was surprised
by how well informed the staffers were in our meetings.”
AIAA will conduct a similar event in the spring of 2001 and AIAA members who are able to participate should
strongly consider attending. Attendance at the CVD is an excellent way to communicate an important message,
and learn a great deal in the process.
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GTTC Ground Testing News
Multimillion-Dollar Construction Project
Completed in the NASA Glenn Icing Research
Tunnel
Contributed by Susan Kevdzija
Over the last year, the NASA Glenn Research Center’s
Icing Research Tunnel (IRT) has undergone a major $5.2million rehabilitation project as part of the Construction
of Facilities program. The scope of the project included
redesign and replacement of the 55-year-old heat
exchanger, addition of fan
outlet guide vanes for flow
across the tunnel cross section reduced to ±1 °F. Flow
angularity and turbulence intensity in the test section
and settling chamber also improved. The achievable
velocity in the test section during icing tests has increased
due to less pressure drop across the heat exchanger and
less frost buildup.
Calibration tests were completed in July 2000, and the
IRT’s first research test program was successfully
completed in early August. With the extensive facility
modifications, the IRT is now well positioned to support
both NASA icing research programs and private industry
customers well into the future.
Hypersonic Tes t Facility at NASA Glenn
Research Center’s Plum Brook Station
Contributed by Mark Woike
conditioning
downstream
of the 25-foot
diameter fan,
and redesign and replacement of the “C” and “D” corner
turning vanes. The purpose of the rehabilitation was to
replace old portions of the infrastructure and to improve
the aerodynamic flow quality in the tunnel.
After the construction phase was completed, the IRT
facility engineers and technician staff successfully
completed the integrated systems testing. Next, a full
calibration of the IRT’s aerothermodynamics and icing
cloud characteristics was completed. Results of these
calibrations indicate that the temperature uniformity
of the tunnel has improved significantly, with variation
The Hypersonic Tunnel Facility (HTF) at NASA Glenn
Research Center’s Plum Brook Station is a freejet wind
tunnel that simulates Mach 5, 6, and 7 true enthalpy
flight conditions
by controlling
t emperature,
altitude, and air
composition. The
overall facility
operating
envelope spans
from 68,000 to
120,000 ft in altitude, 70 to 1200 psia stagnation
pressure, and 2200 to 4200 °R stagnation temperature.
The high stagnation temperatures that are required for
true enthalpy conditions are produced by flowing clean
nitrogen gas through a 3.5-MW electric induction heater.
This heated nitrogen gas is then mixed with clean oxygen
to yield the true air composition of the simulated
environment. The facility has three discrete nozzles 42
in. in exit diameter that are used to set the Mach number
conditions.
The HTF can accommodate test articles up to 10 ft in
length. Plans are in place to expand this capability to 14
ft. The test article is mounted on a thrust stand that can
accommodate up to 8,500 lb of thrust. Liquid
hydrocarbon and gaseous hydrogen propellant systems
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support air-breathing
propulsion testing.
The HTF is currently
the only large-scale
nonvitiated (clean air)
hypersonic
wind
tunnel in the United
States. The facility’s
size and run duration
allow for full systems testing of flight-rated structures
and engines. Recently, the HTF underwent an extensive
rehabilitation. A series of integrated systems tests were
successfully completed in January of 2000, validating the
operational capability of the restored facility. The HTF is
being prepared for a facility calibration program to
validate its calibration and document the flow-field
conditions in the facility. This testing is scheduled for
January and February 2001.
A2I2 GASL Group Receives NASA Recognition
Contributed by Daniel Cresci
The NASA Glenn Research Center recently recognized the
success of the GTX Project (formerly known as
Trailblazer). Members of GASL’s GTX Rig 4 team received
letters of commendation from Mr. Richard A. Blech, Chief
Manager), Michael Celentano (leader for Rig 4 design
and fabrication), Dan Cresci (leader for installation and
testing), Nicholas Tiliakos, Jason Tyll, Patricia Florence,
John Dallaire, Richard Brass, Robert Herold, Carl Sauter,
and Kenneth Truhon.
The team designed, fabricated, assembled, and
instrumented the rig; installed and tested it in GASL’s
Leg IV facility; and helped interpret the data in close
coordination with NASA Glenn’s test team led by Scott
R. Thomas and John D. Saunders. The close teamwork
between NASA and GASL personnel was acknowledged
as a major contributing factor in the success of the
program.
The GTX Rig 4 Test Project is scheduled to continue this
summer, and design and construction of additional GTX
test rigs for use at the NASA Glenn Research Center and
GASL are currently underway.
Boeing to Improve Transonic Wind Tunnel,
Sell Two Others
Contributed by Dennis W. Hergert
Boeing has embarked on a major upgrade to their
transonic wind tunnel facility. The central goal of these
upgrades is to reduce the risk of facility downtime caused
by mechanical and structural failures, and to reduce
operating costs and test cycle times while improving data
quality and productivity.
Boeing’s Wind Tunnel Modernization Initiative is being
conducted in three phases. In 1996, during the first
phase, the drive system was upgraded with a 55,000-hp
motor and an LCI drive system. In addition, the fan
structure was upgraded to replace highly stressed parts
with redesigned components. The electrical and control
systems were also improved to reduce the manpower
needed to run the facility.
Michael Celentano and Dr. Nicholas Tiliakos with the GTX
Test Rig.
of the Engine Systems Technology Branch, and Donald
J. Campbell, Center Director. GTX Rig 4 team members
include Anthony Castrogiovanni (GASL GTX Project
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Currently, during the second phase, the tunnel circuit is
being upgraded. The tunnel shell from just downstream
of the fan to the entrance of the test section is being
replaced with a steel shell. This will reshape the tunnel
aerodynamic lines to reduce power losses and allow
installation of the new tunnel components. A heat
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Wind Tunnel Modernization Initiative
Boeing Transonic Wind Tunnel Planned Improvements
New drive system and fan upgrades 1996
New drive
system
Fan and fan structure
upgrades
Fan nacelle
upgrade
1999
Tunnel air qualities control:
new heat exchanger,
cooling towers, and
dehumidification system
1999
PD ONLY
Not shown:
Systems automation and
improved Mach control
Balance calibration machine
PD ONLY
Plenum flow conditioning
Pitch strut modification
Major
elements
2002
Drive/Fan
Circuit
Balance
Test section
Other
PD ONLY
Test section
walls upgrade
New main balance
New bellmouth and
flow conditioners
1999
exchanger will replace the current air exchanger to
improve control over the tunnel air temperature and
temperature uniformity and to enable cooler operations.
A cooling tower system and a dehumidification system
are being installed to dissipate the heat and reduce the
moisture content of the tunnel airstream.
The tunnel circuit is being extended to accommodate
additional settling distance and provide room for the
improved turbulence reduction system. The current
bellmouth and flow conditioners, located in front of the
test section, will be replaced with a more gradual
bellmouth and a long cell honeycomb for turbulence
reduction. In addition, the aft fan nacelle is being
redesigned to reduce power losses and unsteady flow
coming from the aft fan nacelle and diffuser area. An
integrated control system is being installed to automate
the control of the new equipment being added to the
facility. An acoustic enclosure is also being added to the
new steel portion of the circuit to reduce the ambient
noise levels. New fan blades will be designed, built, and
installed as part of the second-phase upgrade.
Aero Systems Engineering, a division of Celsius Aviation
Services, is responsible for the new design, new
equipment, integrated control systems, and system-level
integration. Boeing’s Facility Asset Management
Organization, through their subcontractors Harris Group
and BAUGH Construction, is responsible for demolition
and construction of the new portion of the tunnel.
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Tunnel air qualities control:
air exchanger eliminated
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Circuit extension
(new circuit-fan
nacelle to bellmouth)
1999
Overall project management is being provided by the
Phantom Works Enterprise Laboratories of The Boeing
Company.
In the third phase, the facility’s external balance, which
is located under the test section, will be replaced to avoid
component failures and facility downtime and to
improve balance measurement accuracy. This upgrade
is targeted for 2002.
As a part of Boeing’s Wind Tunnel Strategy plan, both
the Boeing Supersonic Wind Tunnel (BSWT) and the
Boeing Research Aerodynamic Icing Tunnel (BRAIT) are
being offered for sale. The BSWT is an intermittent
blowdown facility with a 4- by 4-ft supersonic test section
capable of testing models from Mach 1.2 to 4.0 and a 4by 4-ft transonic test section that covers the Mach range
from 0.3 to 1.3. The BRAIT is a closed-circuit low-speed
atmospheric facility capable of testing models from 0 to
250 knots over a temperature range of –45 to 100 °F.
More information on both of these tunnels can be found
on the Wind Tunnel Connection web site (http://
www.worthey.net/windtunnels/).
Boeing’s Dual Aerospike Engines Ready for Test
Contributed by Neil Bosmajian
Boeing’s dual Aerospike engines are ready to begin testing
at NASA’s Stennis Space Center in Mississippi. The
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Aerospike will
power the X–
33, a subscale
technology
demonstrator
that is being
developed as
part of NASA’s
Reusable
Launch Vehicle program. The goal is to greatly reduce
the cost of transporting payloads into low-Earth orbit.
The dual-engine test series follows the highly successful
single-engine hot-fire testing that was performed earlier
this year.
Holloman High Speed Test Track
Contributed by David Minto
The Holloman High Speed Test Track (HHSTT) has been
continuing the Hypersonic Upgrade Program, which will
provide the capability to deliver payloads to targets with
an impact velocity of around 10,000 ft/sec. Fabrication
of the first prototype Hypersonic Upgrade sled has been
completed, and the first test of the design was conducted
in October. The highly instrumented sled provided the
data to verify predicted drags and vehicle and payload
loads. A new 200,000-lb-thrust rocket motor (the Super
Roadrunner) is being developed for the program, and
three prototype motors were poured in September. Two
of the motors were static tested in November. In
December, the third motor was used to propel a
Hypersonic Upgrade sled to 5600 ft/sec in a single stage.
The first- and second-stage pusher sleds that are needed
to reach higher velocities are being fabricated.
Additionally, the Test Track recently completed testing
to evaluate the lethality of the Navy’s Standard Missile–
2 Block IVA, the effectiveness of the Army’s Suite of
Integrated Infrared Countermeasures System, the
accuracy of the Translated Global Positioning System
(GPS) Ranging System, and the ef fectiveness of
improvements to the Air Force’s ACES II ejection seat.
Beech Memorial Wind Tunnel adds Aeroprobe
Contributed by Bonnie L. Johnson
The Walter H. Beech 7x10 Memorial Wind Tunnel has
recently added an Aeroprobe seven-hole probe
(Aeroprobe Corp.) to our inventory of f low
measurement equipment. A new probe traversing system
was also constructed to sweep out the area of interest
behind the wind tunnel models.
The probe traversing mechanism is shown in the
photograph below. The vertical arm determines the
length of the radius of the probe boom. The horizontal
arm determines the angle swept by the probe boom.
We can cover the test section
from 18 in. below the ceiling
of the test section to 18 in.
above the test section’s floor.
The horizontal distance varies depending on the distance
from the ceiling: 20 in. at the top of the boom travel
area and 80 in. at the bottom of the boom travel area.
The illustration shows results taken in horizontal and
vertical increments of 0.5 in. behind a sailboard skeg at
an angle of 4° and a dynamic pressure of 20 lb/ft2. We
can take data from 18 in. aft of the model to 42 in. aft of
the model. The plot was created using Tecplot 8.0.
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Cryogenics Testbed at Kennedy Space Center
Contributed by Eric Ernst
With its one-of-a-kind test facilities, advanced test
equipment and systems, and the multifaceted expertise
of its workforce, Kennedy Space Center (KSC) is an ideal
environment for product development and testing. As a
further enhancement, the Center has developed the
Cryogenics Testbed, which is jointly managed by NASA
and Dynacs Engineering Co., NASA KSC’s engineering
development contractor. The testbed is the result of
collaboration among industry, aerospace, and research
partners. It will provide cryogenic engineering
development and testing services to government,
academic, and commercial organizations.
Elements of the Cryogenics Testbed
• Cryogenics Test Laboratory—This facility includes
three state-of-the-art laboratories, a high bay, and a
class–100 clean room.
• Launch Equipment Test Facility (LETF)—The LETF is
home to a modern machine and fabrication shop to
support advanced prototype development, as well as
large-scale testing apparatus for space launch
systems.
• Material Science Laboratory (MSL)—The MSL
located at KSC provides complete materials
characterization, material development, and failure
analysis capabilities.
In addition to testing of systems and components, the
Cryogenics Testbed supports the design and fabrication
of one-of-a-kind test apparatus. The testbed can supply
liquid nitrogen, oxygen, hydrogen, air, and helium, and
gaseous nitrogen and helium to 6000 psig. Specialized
facilities include pneumatic test circuits and
environmental simulation chambers.
• Low-temperature material evaluation and testing
• High-vacuum pumping and measurements
• Cryogenic systems engineering consultation
• Sensor and instrumentation development
• Large-scale system qualification
• Conceptual design and prototype construction
• Machine and fabrication services
Core lines of work include low-temperature applications
and development of thermal insulation systems,
cryogenic components, and propellant processing
systems. Current programs underway at the testbed
include the following:
• Development and testing of advanced thermal
insulation systems
• Cryogenic ground support equipment flow testing
and analysis
• Advanced launch system umbilical development and
testing, automated umbilical systems development
• Launch pad hydrogen entrapment testing
• Research and development on long-term storage of
cryogens technology for application to Lunar and
Mars missions
• Low-cost, high-efficiency pipeline studies for longdistance transfer of cryogens
• Commercial cryogenic component testing
Potential customers exist in a wide range of scientific
disciplines and industries. The Cryogenics Testbed is
available for project consultation. No matter what size
the project or testing need, the testbed can provide a
unique service on a fixed-price basis to both government
and industry.
F–22 Engine Completes Qualification Test
Milestone for Initial Service Release
Contributed by Thomas Fetterhoff
Testbed Services
• Flow testing
• Leak detection, measurement, and testing
• Insulation system testing using cryostat, tank, or
pipeline test fixtures
• Component development, testing, and evaluation
• Thermal insulation systems testing
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The Pratt & Whitney F119 engine for the Air Force’s new
Lockheed Martin F–22 Raptor air dominance fighter has
successfully met a major Initial Service Release test
milestone.
The Defense Acquisition Board criterion for Initial Service
Release of the Raptor’s engine was to complete half of
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4,330 total accumulated cycle (TAC) tests by December
2000. A TAC is a measure that takes the jet engine from
one power setting to another and then back to the
original setting. The Air Force and Pratt & Whitney team
at the Air Force’s Arnold Engineering Development
Center (AEDC) at Arnold Air Force Base in Tennessee
had completed 2,168 TAC’s on October 31.
Executive Independent Review Team (EIRT). The EIRT is
headed by Dr. Bill Heiser, a former AEDC chief scientist.
Albro said that after the engine has been inspected, it
will be reassembled and go back to SL–2 for additional
RAM sea-level tests. Then it will go to ASTF for altitude
tests to complete the required 4,330 TAC’s before May
31, 2000.
The first part of the test began at Pratt & Whitney’s
Florida test facilities in April, where 750 TAC’s were
accomplished in 246 engine run hours. The test was then
brought to AEDC in July. Initial altitude testing was
conducted in the AEDC Aeropropulsion Systems Test
Facility (ASTF). The ASTF is a unique facility that can
duplicate flight conditions from ground level to 100,000
ft and airspeeds up to Mach 3.8.
“This is a great achievement for the F–22 program and
the Air Force,” said Col. Michael Heil, AEDC commander.
“I am proud that AEDC is playing a role in delivering the
nation’s next-generation air dominance fighter to the
warfighters.” AEDC has been supporting development
of the F–22 since 1989. The F119 engine has been in the
center’s jet engine test facilities regularly since that time.
After approximately 110 engine run hours in the ASTF,
the engine was moved to SL–2, AEDC’s RAM sea-level
test facility (one of four jet engine test cells built at the
AEDC in the 1990’s to replace Navy test facilities that
were located at Trenton, New Jersey). “SL–2 engine
operations were supported seven days per week, three
shifts per day after testing began in late September,” said
AEDC Pratt & Whitney site manager Hugh Horrocks.
“Sverdrup (AEDC test contractor), DOD military and
civilian, and Pratt & Whitney project support personnel
are commended for their contribution to this significant
accomplishment,” Horrocks said.
Jeffrey Albro, a Navy employee at Arnold and AEDC F119
program manager, said, “AEDC and Pratt & Whitney test
teams have done a superlative job of supporting an
ambitious test schedule to get to the required milestone.
We tested six days a week, essentially around the clock,
and took day seven for facility, engine, and people
maintenance.” Albro said test objectives included
performing base lining back-to-back calibrations from
the ASTF test cell to SL–2 to document performance of
the engine before the start of accelerated mission tests,
and completing high-cycle fatigue and accelerated
mission tests. Testing in SL–2 took approximately 333
hours of engine run time.
According to Albro, now that the engine has completed
its first goal, it will be removed from the test cell and
disassembled for evaluation by Pratt & Whitney and an
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“AEDC and Pratt & Whitney test
teams have done a superlative
job of supporting an ambitious
test schedule to get to the
required milestone. We tested
six days a week, essentially
around the clock, and took day
seven for facility, engine, and
people maintenance.”
Aerodynamic and weapons carriage and release tests have
also been accomplished in the center’s large and small
transonic wind tunnels.
Pratt & Whitney has maintained a field office at AEDC
for more than 30 years. United Technologies Corp. (Pratt
& Whitney’s parent corporation) and AEDC signed a 20year alliance contract in 1992. Pratt & Whitney engines
tested in the last decade at AEDC include the F119 for
the F–22, F119 derivatives for both the Boeing and
Lockheed Martin candidates for the Joint Strike Fighter,
and F100 engines, which power F–15 and F–16 aircraft.
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Wright Flyer Model B Airfoil Testing
Contributed by Drew Landman
The Wright Experience, Old Dominion University (ODU), Wichita State University, and NASA Langley Research
Center (LaRC) cosponsored two wind tunnel tests on a Wright model B airfoil geometry. The model B airfoil test,
under the direction of ODU’s Dr. Drew Landman, was part of a program to
evaluate the aerodynamic performance of early Wright aircraft. The model B
was chosen as the first test article because it was the Wrights’ first production
aircraft and has the most complete engineering specifications and documentation. With completion of the wind tunnel tests, Ken Hyde of the Wright
Experience plans to fly the model B to improve his understanding of its handling qualities and gain familiarity with the controls. The overall test program,
directed by ODU’s Dr. Robert Ash, will proceed by moving back in time to
test first the 1905 Flyer and, finally, the 1903 Flyer. The Wright Experience was
chosen by the Experimental Aircraft Association to build an exact, flightworthy reproduction of the 1903 craft for the National Park Service’s centennial
celebration of the Wrights’ first flight at Kitty Hawk. Propeller tests and now
airfoil tests have been completed. A full aircraft test is slated for the Langley
Full-Scale Tunnel in summer 2001.
The airfoil testing was done using two models, a full-scale fabric-covered replica and a one-third-scale solid-surface model with pressure orifices. Since the
model B did not use rib stitching on the top surface, researchers had some
doubts about the legitimacy of using a solid-surface model for all testing. The
chord of the aircraft wing was 74 in., so testing at full-scale in available twodimensional airfoil facilities would have to be limited to low angles of attack
to avoid excessive boundary corrections. The data for higher angles of attack
were obtained using a smaller scale model; those data will be combined with
the full-scale test data to provide the complete story.
The full-scale testing program was completed in the Wichita State Walter H.
Beech 7x10 Memorial Wind Tunnel in August 2000. Lift and pitching moment were obtained at the flight Reynold’s number with a floor-to-ceiling
balance system, and drag was evaluated using a wake rake. Flow visualization using tufts helped reveal stall patterns.
Many thanks go out to Ms. Bonnie Johnson, Director of Aerodynamic Laboratories at the National Institute for
Aviation Research, for her support of this project and help during the test.
The one-third-scale testing was completed at the NASA LaRC Low-Turbulence Pressure Tunnel (LTPT) in October
2000. The lift and pitching moment data were obtained by integrating surface pressures, and drag was measured
with a rake wake. All runs were made at the flight Reynold’s number, again using flow visualization with tufts to
evaluate stall behavior. The Wright Flyer program is grateful to the many NASA LaRC employees who helped make
this test possible, including Dr. Jerry Kegelman, Mr. Long Yip, Mr. Frank Quinto, Ms. Pam Phillips, and Ms. Ruth
Martin. Mr. Juan Cruz and Mr. Brad Crawford were very helpful during the one-third-scale model design and construction process.
At the time of this writing, Mr. Julian Alvarez, graduate assistant in the ODU Aerospace Engineering Department, is
sorting through the reams of data acquired during the tests. Stay tuned for further reports on this exciting endeavor.
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Formal Experiment Design in Wind Tunnel Testing
Contributed by Dick DeLoach
NASA Langley has been experimenting with a new approach to wind tunnel testing called the Modern Design of
Experiments (MDOE). “Randomization,” a key MDOE concept, is discussed in a brief article for the lay reader
available from the author at R.DeLoach@larc.nasa.gov. Condensed excerpts follow.
Ronald Fisher and colleagues had formulated the basic rules of modern experimentation by 1935, the year he
published his landmark book, “The Design of Experiments.” These rules, comprising a set of well-defined procedures
to ensure objective inferences from empirical research, stress the importance of randomizing the order in which
independent variables are set in an experiment. There are many reasons for disappointing wind tunnel test results,
but one that we don’t often consider is our failure to follow Fisher’s randomization prescription in wind tunnel
testing. Systematic variations in time can lead us to mischaracterize the influence of independent wind tunnel
variables like angle of attack on response variables such as lift, drag, or pitching moment. Randomization defends
against such effects.
Suppose, for example, that while we are acquiring a polar, some very subtle, systematic change occurs in flow
angularity. Suppose this causes earlier points in the polar to be biased as slightly low and later points to be biased
as slightly high. (Such effects become important whenever they consume a significant fraction of the error budget,
which can easily occur in high-precision wind tunnel testing.) This unknown, systematic variation will rotate and/
or distort conventional polars in which the alpha values are set sequentially in time. If we are unaware of the withinpolar flow angularity changes, then every nuance in the polar will be attributed exclusively to alpha effects, even
though flow angularity effects are responsible for some of them. Complex structures in certain conventional pitch
polars may be due to just such unknown systematic variations, confounding less exotic underlying alpha effects.
When these systematic variations occur between polars, they can also cause displacements, or bias shifts from one
polar to the next (in addition to using randomization, MDOE practitioners cope with these effects with another
technique known as “blocking”).
Systematic variation also causes measurement errors to be correlated and thus not independent of each other, as
would be required for valid standard precision interval computations and other common variance estimates. Even
relatively mild correlation can corrupt variance estimates by an order of magnitude or more, introducing substantial
errors into estimates of “95-percent-confidence intervals” and other such quality metrics.
Here’s how randomization works: It ensures that the systematic error at a given angle of attack is equally likely to be
either positive or negative (relative to the mean systematic variation) depending entirely on whether that angle of
attack was set early or late in the randomized polar. The error in the next angle-of-attack level will likewise have an
equal chance to be positive or negative, depending on whether it was set early or late. So randomization converts
unseen systematic error to an additional component of ordinary random error that is easy to detect and easy to
correct, by replication and other means.
Fisher randomized as if there were some systematic variation in any given experiment, even when he had no specific
reason to suspect that there was. He did this to be sure of the correct cause-and-effect relationship between his
dependent and independent variables. MDOE wind tunnel practitioners always randomize for precisely the same
reason. Without randomization, it would be difficult to be sure of the correct relationship between response variables
(e.g., forces and moments) and independent variables such as angle of attack.
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Vol 4 No 1
January 2001
GTTC Committee News
USAFA’s Eagle Peak
2000 Summer Golf Scramble is a Huge Success!
Six hardy souls braved the elements of the Rocky
Mountains for the alternative Thursday afternoon
activity. Jean Bianco, Dennis Hergert, Tom McLaughlin,
Julie Morrow, Mark Perry and Mat Rueger drove down
to the U.S. Air Force Academy to climb Eagle Peak, a 9,368foot mountain rising to the west of the cadet area. The
monumentally steep trail followed Goat Camp Creek for
a mile. In many places, the trail was so steep hands were
required to scramble up the slope. At about 8,800 feet,
the trail flattened out into a beautiful aspen grove and
meadow full of Colorado columbine and Indian
paintbrush. After the wildflower meadow, it was an even
steeper climb over loose dirt and huge boulders another
quarter of a mile to the top. Though it was a tough hike,
all climbers summitted, including Mat “you go ahead,
I’m going back” Rueger. Everyone was rewarded with
breathtaking panoramic views of Pikes Peak, the Front
Range Rockies, the entire Air Force Academy, and perhaps
even Kansas.
The first annual GTTC summer golf scramble was held at
the lovely Englewood Municipal Golf Course located in
beautiful Englewood, Colorado (don’t let the fact that
the front nine holes are built on a garbage dump fool
you!). There were four teams competing for fabulous
prizes such as golf ball sleeves and a full year of bragging
rights. Besides overall lowest score, there were two longest
drive and three closest-to-the-pin awards. The two
powerhouse long-drive winners were Dan Marren on
hole 2 and Allen Arrington on hole 15. The golfers
showing pinpoint accuracy on the par 3s were John
Lafferty on holes 4 and 10 (of course, he was using Nancy
Swinford’s clubs) and John Magill on hole 17. The lowest
overall score was earned by the team of John Magill, Dave
Minto, Mark Rennie, and Frank Steinle, an impressive 5
under par. Although the competition was stiff, a fun time
was had by everyone. Congratulations to all who
participated! And remember, without the losers, there
wouldn’t be any winners!
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Vol 4 No 1
January 2001
GTTC Calendar of Upcoming Events
2001
January 8 to 11
39th AIAA Aerospace Sciences Meeting and Exhibit; Reno, NV
March 21 to 22
AIAA Congressional Visits Day
March 16
Abstracts due for GTTC Student Engineering Contest
April 1
Input due for AIAA GTTC Newsletter
April 15
Nominations due to AIAA for Associate Fellow
May
Abstracts due for 40th AIAA Aerospace Sciences Meeting and Exhibit
May 4
Final reports due for GTTC Student Engineering Contest
July 8 to 11
37th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit; Salt Lake City, UT
August 1
Input due for Aerospace America Highlight December issue
October 1
Nominations due for AIAA Ground Testing Award
November 1
Nominations due to AIAA for TC membership
November 1
Input due for AIAA GTTC Newsletter
December 1
Aerospace America Highlights Issue
2002
January 14 to 17
40th AIAA Aerospace Sciences Meeting and Exhibit; Reno, NV
June 24 to 27
22nd AIAA Advanced Measurement Technology and Ground Testing Conference;
St. Louis, Missouri
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GTTC Newsletter
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Vol 4 No 1
January 2001
Request for GTTC Membership Information
The purpose of the Ground Testing Technical Committee (GTTC) is to advance the state of the art and technologies
associated with ground testing and ground testing facilities. The scope of the committee’s interests includes duplication
and simulation of aerodynamic and aerospace flight environments for the testing of aerospace systems, subsystems, and
components. The ground test facilities of interest include wind and shock tunnels, ballistic and high-speed test track
ranges, space environment facilities, and aeropropulsion test facilities.
The GTTC is composed of approximately 35 to 40 AIAA professionals from commercial, government, and academic sectors
representing the technical spectrum for state-of-the-art ground testing of aerodynamic, propulsion, and space systems.
The Committee continually seeks members from all parts of the ground testing community.
The membership term on the GTTC is 4 years with approximately 25 percent of the membership rotating off each year.
Prospective members should be willing to make a commitment to GTTC activities and attend the semiannual GTTC meetings.
If you are interested in receiving further information concerning membership in the GTTC, please fill out the form below
and mail to
E. Allen Arrington
Dynacs Engineering, MS 6–2
NASA Glenn Research Center
Cleveland, OH 44135
216–433–8507
fax 216–433–8551
Name:
Title:
Company:
Address:
City:
State:
Zip:
Phone:
Country:
E–mail:
Professional responsibility:
Professional membership: AIAA
Years experience:
SAE
ASME
ITEA
Other
Educational background (degree, discipline, year):
Prior service on AIAA Technical Committees:
Name:
Prior experience organizing conferences, sessions, short courses:
Area of interest: Aerodynamics
Aeropropulsion
Space systems
Does your company currently support other AIAA Technical Committees?
Other comments:
M–0702
Nov 00
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