2016 NATIONAL WING DESIGN COMPETITION RULES
These competition rules are modeled after the rules for the international AIAA Design/Build/Fly
competition, which can be found at www.aiaadbf.org.
The competition rules may be changed or supplemented at any time.
Notification of any rule changes or clarifications will be disseminated via email to teachers or
team liaisons and posted at:
http://airandspace-ed.org/program/competitions/nasei-wing-design-competition/
Contents
Contents .......................................................................................................................................... 1
Summary of Changes ...................................................................................................................... 3
Competition Summary .................................................................................................................... 4
Judging ............................................................................................................................................ 4
Competition Site ............................................................................................................................. 5
Team Requirements ........................................................................................................................ 5
Schedule .......................................................................................................................................... 5
Communications ............................................................................................................................. 6
Aircraft Requirements ..................................................................................................................... 7
General ........................................................................................................................................ 7
Safety........................................................................................................................................... 8
Scoring ............................................................................................................................................ 9
Design Challenge .......................................................................................................................... 10
General ...................................................................................................................................... 12
Payloads .................................................................................................................................... 12
Flight Line Order .......................................................................................................................... 13
Mission.......................................................................................................................................... 13
General Mission Specifications ................................................................................................. 14
Flight Course ............................................................................................................................. 14
Contingencies ................................................................................................................................ 15
Report Guidelines ......................................................................................................................... 15
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Design Report:........................................................................................................................... 16
Design Report Electronic Copy: ............................................................................................... 17
Appendix A: Airfoil Ordinates ..................................................................................................... 18
Appendix B: Eppler 422 Airfoil Characteristics ........................................................................... 21
Appendix D: Martin Hepperle 114 Airfoil Characteristics........................................................... 25
Appendix E: NACA 62(1)-212 Airfoil Characteristics ................................................................ 27
Appendix F: Selig/Donovan 7043 Airfoil Characteristics ............................................................ 29
Appendix G: USA-35B Airfoil Characteristics ............................................................................ 31
Appendix H: PVC Pipe Dimensions ..............................................Error! Bookmark not defined.
Payload 1 ....................................................................................Error! Bookmark not defined.
Payload 2 ....................................................................................Error! Bookmark not defined.
Payload 3 ....................................................................................Error! Bookmark not defined.
Payload 4 ....................................................................................Error! Bookmark not defined.
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Summary of Changes
The format of this year’s competition has changed. Please read the rules carefully and be aware
of all changes. The following document changes from the previous year’s competition:
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Competition Summary: Design report due date
Competition Site: Competition date
Schedule: Design report due date
Communications: New website where information will be posted
Aircraft Requirements: All payloads must be mounted on wing; Mounting hardware that
counts towards wing weight limited to non-removable components; website location for
self-inspection checklist changed
Scoring: Two separate Flight Scores may be recorded for each of two unique payloads;
Report Score will be scaled from 100 to 20 points max; Student pilot bonus increased to
10%
Design Challenge: Mission changed drastically to a multi-role payload mission; 2 out of
a predetermined set of 4 unique payloads will be flown during the competition
Payloads: Four unique payloads are detailed and must be supplied by the team; At their
discretion, teams may also supply their own additional “counterweight” payloads
Mission: Each team must supply student or non-student volunteers to serve 30-minute
rotations as Flight Course spotters
Contingencies: Teams may only use one competition wing to record valid Flight Scores
even if a second wing is identical to the first
Report Guidelines: Design report due date
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Competition Summary
The National Wing Design Competition (NWDC) is sponsored by the National Air & Space
Education Institute (NASEI) and is intended to provide an introduction to aircraft design. The
University of Kentucky College of Engineering and NASA have provided support for this year’s
NWDC. Engineering firms such as Stantec, Lockheed Martin and Belcan will also support the
NWDC. Student teams will design, fabricate, and demonstrate the flight capabilities of a wing
to replace the stock Hobbico® NexSTAR™ wing.
The goal of the competition is to design and build a high-performance wing, while demonstrating
a balance between practical-and-affordable manufacturing techniques and good flight
characteristics. The design objective is to produce a multi-role wing that, when mounted on the
NexSTAR™ fuselage is light weight, and can carry a diverse array of non-uniform payloads at a
distance from the center of gravity of the aircraft. The wing must be capable of carrying
different specified payloads non-concurrently. Scoring for each sortie is a function of the
position of the particular external payload with respect to a fixed point on the NexSTAR™
fuselage and the overall weight of the wing.
It is the responsibility of each team to know and follow all rules, updates, and competition
day briefings. In the aircraft industry, deadlines are common and meeting these deadlines is
extremely important. Thus, all competition deadlines will be enforced with a graduated score
reduction penalty outlined here in the “Schedule” and “Report Guidelines” sections. Also, teams
are required to submit a Design Report that describes the design process. The Intent of the report
is to represent a wing “proposal” explaining the team’s design choices including cost-benefit
analyses, tradeoffs, optimizations, etc. The reports are not explanations of test results and can be
comprehensively written before flight testing even begins. However, if flight tests are
accomplished before the due date, observations of results may be included in the report. Reports
are due Friday, April 29, 2016.
Judging
Each team must design, document, build, and fly a competition wing. Flight Scores will be based
on the demonstrated mission performance obtained during the competition.
Each team must submit a Design Report describing their design and outlining their proposed
construction process. A maximum of 20 points will be awarded for the Design Report. Reports
will be scored by a panel of aerospace industry professional engineers and professors.
The overall team score is the product of the Report Score and Flight Score.
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Competition Site
The exact competition date and location is to be determined, although it is tentatively scheduled
for Saturday May 14 2016 at Lake Cumberland Regional Airport in Somerset, KY. The
competition location and schedule will be posted on the NASEI website, and all teams will be
notified of changes via e-mail. To obtain atmospheric data for flight planning and design
purposes, you can check historical weather conditions at www.weatherbase.com or
www.weatherunderground.com.
Team Requirements
All team members (except for a non-student pilot) must be NASEI students. Teams may use a
non-student pilot if desired. All pilots (student or non-student) must be AMA members and must
perform the technical inspection of their team’s aircraft and complete a signed proof of flight
form prior to the competition.
Each school may enter only one team. Each team must have its own airframe. This consists
of a fuselage, tail, landing gear, propulsion system, and receiver. Each wing has a total spending
limit of $700 dollars. Each team is eligible to be reimbursed for up to $350 of these expenses by
NASEI. Valid expenses may be invoiced to NASEI by submitting itemized receipts along with a
written explanation of items purchased to the following address by May 14, 2016.
National Air & Space Education Institute
2720 Cannons Lane, Hangar 7
Louisville, KY 40205
Schedule
Design Reports must be submitted to NASEI.Wing.Design.Competition@gmail.com by 5pm
eastern daylight time on April 29, 2016. No corrections, additions, or changes can be made after
submission. Teams must submit one electronic copy of their Design Report in PDF format.
A 5% reduction in score will be applied every 24 hours to reports submitted after the 5pm April
29 deadline. For example, the maximum possible score for a report submitted at 6pm on April
30 will be 90%.
The competition is tentatively scheduled for May 14, 2015. The competition is anticipated to run
from 9am to 3pm. A final competition schedule will be e-mailed to the teams prior to the
competition date and posted on the NASEI web page. If the competition is postponed due to
weather, then the competition will be rescheduled and the same competition schedule will be
followed.
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Communications
The competition administrators will maintain a website as a resource for downloading the latest
information regarding the competition. This website can be found at:
http://airandspace-ed.org/program/competitions/nasei-wing-design-competition/
Questions regarding the competition may be sent to the competition administrators by e-mail at:
NASEI.Wing.Design.Competition@gmail.com
All correspondence with the competition administrators should include a team name and school
name. All questions and answers will be entered periodically into FAQs and posted on the
competition website.
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Aircraft Requirements
General
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The wing design may be of any form except a flapping wing configuration.
The wing must be separable from the aircraft.
All payloads must be mounted to the wing; not to the aircraft fuselage. Any payload
mounting hardware that is not removable will count as wing weight. For example, if
payloads are mounted on a threaded bolt that is integral to the wing frame and secured
with a wing nut, then the bolt counts as wing weight, but the wing nut does not.
Any lifting body added to the original NexSTAR™ airframe counts as a wing and must
be removable. For example, if a bi-plane design is used, both wings must be removable.
All parts used to attach the wing to the airframe count toward the weight of the wing. For
example, if a main spar is used to secure the wing to the airframe, then it counts toward
the weight of the wing (even if part of it lies inside the fuselage).
Wing struts count as part of the wing and must be removable.
No structure or components may be dropped from the aircraft during flight.
No form of externally assisted take-off is allowed. All energy for take-off must come
from the unmodified O.S. Engine included in the kit.
Engine fuel must be 10% Nitro-methane.
Each aircraft must use a commercially made propeller provided in the kits (replacement
propellers may be purchased if necessary). Teams may modify the propeller by clipping
the tips or painting the blades for balance. Other modifications are not allowed.
Aircraft and pilot must be Academy of Model Aeronautics (AMA) legal. This means:
o The aircraft take-off gross weight with payload must be less than 55-lbs.
o The pilot must be a member of the AMA.
o Complete AMA Aircraft Safety Code can be found at:
http://www.modelaircraft.org/files/105.pdf
THE COMPETITION AIRCRAFT MUST BE FLOWN PRIOR TO THE
COMPETITION. TEAMS MUST SUBMIT THE PROOF OF FLIGHT FORM
SIGNED BY AN AMA MEMBER, AS WELL AS A PHOTOGRAPH OR VIDEO
OF THE AIRCRAFT IN FLIGHT IN ORDER TO FLY IN THE COMPETITION.
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Safety
Proof of flight of the NexSTAR™ platform with the competition wing MUST be verified by the
competition organizers prior to being able to fly. This requirement is to ensure competition
safety. Aircraft without the signed proof of flight form will not be allowed to fly at the
competition. All decisions made by judges are final.
All aircraft will be self-inspected prior to each test flight and competition flight by the team’s
AMA certified pilot. The purpose of this inspection is to ensure the safety of all people and the
aircraft. Aircraft deemed unsafe will not fly.
The quick pre-flight self-inspection checklist is posted on the WDC website at http://airandspaceed.org/program/competitions/nasei-wing-design-competition/pre-flight-self-inspection-checklist.
In
detail, the inspection will consist of the following:
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Brief review of key structural points of aircraft
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Wing tip test: Aircraft with full flight payload will be lifted from a lift point at each wing
tips (to roughly simulate a 2.5g load case) to verify adequate strength and to check for
vehicle center of gravity (cg) location. Teams should mark the expected empty and
loaded cg locations on the exterior of the aircraft. Special provisions should be made for
aircraft whose cg does not fall within the wing tip chord so the aircraft can be secured
while performing the wing tip test.
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Radio range check (motor on and motor off) and fail safe check. All aircraft radio
transmitters must have a fail safe mode, which is automatically selected if the receiver
loses signal from the radio transmitter. The fail safe should be demonstrated on the
ground by switching off the transmit radio. During failsafe the aircraft receiver must
select Throttle Closed.
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Physical Inspection:
o Verify all components are adequately secured to vehicle. Verify all fasteners are
tight and have either safety wire, locktite (fluid) or nylock nuts. Clevises on flight
controls must have an appropriate safety device to prevent disengaging in flight.
o Verify the structural integrity of the propeller and ensure proper propeller
attachment.
o Visual inspection of electronic wiring to assure adequate wire gauges and
connectors.
o Verify all control surfaces move correctly.
o Check the integrity of the payload and payload attachment system.
Any minor damage sustained during a flight attempt may be repaired. However, an aircraft must
be re-inspected by the team’s AMA certified pilot after repairs before being cleared to fly.
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Scoring
Each team's score will be computed from the Report Score and Flight Score using the formula:
Score = Report Score * [(Flight Score A) + (Flight Score B)] * 1.1 (Student Pilot Bonus)
There are 4 unique predetermined payloads that each team may be asked to fly in the 2016
competition. These payloads are detailed in the following section. At the beginning of the
competition, 2 of the 4 payloads will be randomly selected. Each team will have a maximum of
two attempts to complete a successful flight carrying both of the 2 selected payloads nonconcurrently (two attempts for payload 1 and two attempts for payload 2). Flight Scores A is
awarded for a successful flight carrying payload 1. Flight Score B is awarded for a successful
flight carrying payload 2. If a team is unable to complete a successful flight carrying either
payload, a Flight Score of zero will be recorded for that payload. If a team is unable to complete
a successful flight of either of the two selected payloads on the day of the competition, their
overall score will also be zero per the equation above.
The Flight Score equation is described in the following section. The number of payloads is not
considered in the Flight Score equation. Each team is only required to fly one instance of each
of the two selected payloads. Additional points will not be awarded for carrying multiple
instances of the same payload concurrently. However, additional payloads of any design may be
mounted to the wing for any flight attempt in order to maintain aircraft weight and balance. Any
such “counterweight” payloads must be mounted to the wing and not the fuselage. All such
“counterweight” payloads that are removable from the wing will not count as additional wing
weight. The Student Pilot Bonus will only be awarded to teams that complete a successful flight
at the competition piloted by an AMA-certified student member of the team for either Flight
Score A OR B. The student pilot is not required to complete two successful flights in order for
the bonus to be awarded.
The Report Score rubric that judges will use (outlined in the “Report Guidelines”) is based on a
100 point system. These scores will be scaled down to a maximum of 20 points when factored
into the overall score equation above. This is intended to account for minor disparities in report
grades recorded by a variety of industry professional judges. As such, report scores of 96 thru
100 will be scaled to 20; scores of 91 thru 95 will be scaled to 19; and so on.
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Design Challenge
Multi-Role Adaptive, Light-Weight Wing
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This is a strategic weight and balance mission. Just as commercial and military aircraft
must be trimmed and balanced for a multitude of potential cargo or armament
configurations, your wing must be capable of carrying a variety of payloads in
challenging locations.
The 4 unique payloads that may potentially be flown at the competition are detailed here.
Two of these 4 payloads will be randomly selected at the beginning of the competition.
Each team is required to manufacture and provide their own payloads for the competition.
1) Payload 1: As many schools already have an abundance of them, the first
payload is the same as in last year’s competition. A single payload of 1½”
diameter Schedule 40 PVC pipe cut to 24” in length. The pipe must have a ¼”
diameter hole drilled perpendicular to the axial length that extends through
both walls. The ¼” hole must be drilled at the midpoint of the pipe’s length.
The ends of the pipe must be covered. The weight and size of the covering is
at the discretion of the team.
2) Payload 2: The second payload consists of two 1 ½” diameter Schedule 40
PVC pipes. One pipe is cut to 24” in length, and the other pipe is cut to 36” in
length. The pipes must have a ¼” diameter hole drilled perpendicular to the
axial length that extends through both walls. The ¼” hole must be drilled at
the midpoint of the pipe’s length. The ends of the pipes must be covered. The
weight and size of the covering is at the discretion of the team.
3) Payload 3: The third payload is 30 US pennies. Additional structures may be
used to carry the payload. These additional structures must be removable, or
these structures are included in the wing weight.
4) Payload 4: The fourth payload is 16 ounces of water. Additional structures
may be used to carry the payload. These additional structures must be
removable, or these structures are included in the wing weight.
All payloads (including “counterweight” payloads) must be externally mounted to the
wing and must be removable. The mounting locations of all payloads are left to the
discretion of each team, but the locations of the primary payloads DO impact the Flight
Score. The number and location of any “counterweight” payloads DO NOT impact the
Flight Score
All mounting mechanisms not specified in the payload descriptions above are at the
discretion of the teams, but the mounting must be deemed safe by an AMA member.
Any mounting structure that is not removable will be included in the wing weight.
Flight Scores are recorded after successful flights as follows:
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𝐹𝑙𝑖𝑔ℎ𝑡 𝑆𝑐𝑜𝑟𝑒 =
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(3)𝐷𝑥 + (2)𝐷𝑦
𝑊
𝑊 is the wing weight in pounds. 𝐷𝑥 is the distance in inches from the nearest surface of
the primary payload to a fixed y-z plane along the length of the stock Hobbico®
NexSTAR™ fuselage as shown in Figure 1. 𝐷𝑦 is the distance from the nearest surface
of the primary payload to the aircraft thrust line in inches. Note that if the total payload
consists of multiple payload objects (e.g., Payload 2), then 𝐷𝑥 and 𝐷𝑦 are the minimum
distances to either payload object. A successful flight must be completed in order to
obtain the above Flight Score.
If multiple instances of the primary payload are flown concurrently, the Flight Score will
be recorded with respect to the location of the single instance of the payload that results
in the lowest Flight Score per the equation above.
Teams are responsible for knowing their wing weight, payload location measurements
and keeping their own score. Two hypothetical primary payload locations and their
respective measurements are shown in Figure 2.
Figure 1: Origin of Dx Measurements
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Figure 2: Example Primary Payload Location Measurements
General
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Teams may use any airfoil to design their wing. A list of airfoil coordinates is available
at http://aerospace.illinois.edu/m-selig/ads/coord_database.html. Note that this website
gives airfoil coordinates only, it does not provide aerodynamic data.
Aerodynamic data is provided in Appendices A thru G for the following airfoils:
Eppler 422 (E422)
Eppler 423 (E423)
Martin Hepperle 114 (MH 114)
NACA 62(1)-212
Selig/Donovan 7043 (SD 7043)
USA-35B
Teams are responsible for gathering the aerodynamic data for airfoils other than those
provided in the appendices of this document.
Teams may not use the wing provided in the NexSTAR™ kit.
If teams use airfoils other than those provided by the WDC rules the aerodynamic data
and detailed discussion of the choice must be provided in the design report.
All design decisions made must be discussed in the Design Report.
The Design Report must describe the expected fabrication procedures.
Each team is required to use the standard fuel and propulsion system.
Payloads
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Each team is responsible for providing all payloads.
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The payloads must be secured to ensure safe flight without possible variation of aircraft
center of gravity during flight.
Payloads must be carried externally and mounted to the wing.
All payload mounting locations must be inspected by an AMA member for safety as part
of the pre-competition technical inspection.
Flight Line Order
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Each team’s position in the flight order is determined from their Report Score; the highest
Report Score goes first. The order of teams with the same report score will be determined
by coin toss. The flight order is repeated after all teams have had an opportunity to fly.
There will be a staging area position near the flight line. If you are not ready to enter
a staging area when it is your turn, then you forfeit that opportunity to fly.
o Electing to enter one of the staging area positions on your turn in the rotation
order will constitute using a flight attempt.
o If you go to the flight line and are not able to begin your flight when instructed,
then you forfeit that flight attempt.
The NexSTAR™ with the designed wing assembled, fueled, and ready to fly must be
brought to the staging area prior to the flight.
Only the pilot and one observer are allowed to enter the staging area.
The observer is allowed to leave the staging area to retrieve forgotten equipment, but
must return to the staging area prior to the flight attempt. If both the pilot and the
observer are not in the staging area when the flight attempt is called to start, then the
flight attempt is forfeited.
Mission
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Each team will be allowed a maximum of 4 flight attempts (two attempts for each of the
two primary payloads selected the day of the competition). Teams may not use more
than 2 attempts for any one payload.
Aircraft must perform a conventional takeoff.
Teams are allowed 2 takeoff attempts per flight attempt. If the team has not completed a
successful takeoff after the 2nd attempt then the flight attempt is forfeited. No repairs
may be made between takeoff attempts.
The aircraft must complete two laps of the flight course shown in Figure 3 before
landing.
After completing the required number of laps of the flight course for a given mission, goarounds are permitted if necessary for safe landings.
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The aircraft must complete a successful landing at the end of a mission to receive a Flight
Score. A successful landing is outlined in the general mission specifications below.
General Mission Specifications
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The engine may run only when the aircraft is on the runway, in flight, or in the
designated engine run-up area and under certified AMA member supervision.
Maximum flight crew is the pilot and one observer.
The observer must be a student. The pilot may be a non-student.
The aircraft must be loaded, fueled, and ready when called to fly.
Each team must provide two volunteers to serve 30-minute rotations as flight course
spotters. Volunteers may be students or non-students.
The upwind turn will be made after the upwind spotter signals the observer by raising his
or her hand. The downwind turn will be made after the downwind spotter signals the
observer. Upwind and downwind spotters will be positioned 500 ft from the starting line.
Aircraft must be straight and level when passing the turn marker before initiating a turn.
Aircraft must pass the start/finish line in the air. Then they may land immediately or go
around at the pilot’s discretion.
Aircraft must land on the runway. Aircraft may "run-off" the runway during rollout. Aircraft may not “bounce” off the runway.
Aircraft obtaining “significant” damage during landing will not receive a score for that
flight. Damage that is “significant” would prevent the aircraft from taking off again
without repairs. Final determination of “significant” damage is at the discretion of the
Flight Line Judge.
Flight altitude must be sufficient for safe terrain clearance and low enough to maintain
good visual contact with the aircraft. Decisions on safe flight altitude will be at the
discretion of the Flight Line Judge.
Flight Course
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The orientation (direction) of the flight course will be adjusted based on the prevailing
winds as determined by the Flight Line Judge. The flight course will be positioned to
maintain the greatest possible safety. The nominal flight course is shown in Figure 3.
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Figure 3: Flight course for the competition. Not drawn to scale.
Contingencies
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In the event that, due to time or facility limitations, it is not possible to allow all teams to
have the maximum number of flight attempts, the competition committee reserves the
right to ration flight attempts (as determined by the competition committee).
In the event of a tie in the final score, the team with the higher Report Score will place in
front of the other team.
Teams may perform repairs on their wings between flight attempts and continue to
compete provided the repaired wing passes inspection by a certified AMA pilot. Each
team may only enter one competition wing. Flight Scores will not be recorded for flights
using a second wing even should that wing be identical to the first.
Report Guidelines
In engineering practice, construction does not begin until the design has been finalized, a
thorough analysis has been conducted to verify that the final product will function as intended
and the construction and testing processes and procedures have been thoroughly planned. The
purpose of these design reports is to document design decisions as well as the analysis of
tradeoffs behind those decisions. This report is not intended to be a summary of construction
progress. The judges evaluating the reports will base their scores on how well you document
your design and analysis, on the suitability of the analysis for ensuring that you achieve the best
possible flight score, on how well you have planned out the construction procedures and how
well you’ve thought out what flight tests need to be conducted to ensure that your aircraft can
safely fly with each of the 4 design payloads.
Reports should adhere to the following requirements. Failure to meet requirements may result in
score reduction.
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Due 5pm EST Friday April 29, 2016 (a 5% score reduction will be applied every 24
hours to late reports)
Reports should be 5 to 10 pages.
Reports should have a cover page (which includes school and team name), table of
contents, and list of references, none of which count toward the 5-10 page count.
Reports should include CAD drawings, which do not count toward the 5-10 page count.
However, these pages must contain drawings only.
Reports should be typed single sided.
Reports will receive a 10 point penalty for each page under 5 or over 10.
All reports should be at least 1.5 spacing and no more than double spaced, 10-pt Arial
font. Tables and figures should also be at least 10-pt Arial font. Margins should be 1 inch
on all sides. All figures and tables should be clear and readable for the judges. Format
and readability will be considered in the scoring of the reports.
Design Report:
1) Executive Summary (10 points):
 (4pts) Provide a summary description of your design, and explain why it is the best
solution for the mission requirements.
 (2pts) Describe the mission requirements that impact your design.
 (2pts) Document the predicted performance of your wing and discuss the wing
characteristics you sought to optimize
 (2pts) Detail the tradeoffs you anticipate (consider weight reduction, ease of production,
etc.)
2) Wing Parameter Design (45 points):
 (6pts) Describe mission requirements and resulting design requirements.
 (8pts) Provide a detailed review of the solutions that were considered (i.e. airfoil
selection, planform selection, wing sizing) and show a comparative analysis of 3 or more
wings considered and why you selected the one you did.
 (8pts) Tabulate final wing dimensions and characteristics (i.e. airfoil choice, span, surface
area, taper, aileron sizes, dihedral and any key characteristics describing your final wing
design – see Aerodynamics Module on NASEI/IAE website).
 (5pts) Provide estimates of predicted performance characteristics for final design (i.e. lift,
drag, stall, etc. – see equations in Aerodynamics Module on NASEI/IAE website)
 (8pts) Document the weight and balance for final design. Must include a weight &
balance table for the empty aircraft and with payload. (see NASEI aeronautical course on
Moodle)
 (6pts) Provide engineering drawings of final wing design and components.
3) Manufacturing Plan and Processes (35 points):
 (10pts) Document the process selected for manufacture of major components and
assemblies of the final design.
 (10pts) Detail the manufacturing processes investigated and the selection process/results
including cost-benefit analyses to consider such factors as time, money, strength and
weight.
2015 WING DESIGN COMPETITION
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(15pts) Include a manufacturing milestone chart, preferably a Gantt chart, showing
scheduled and actual event timings. It is ok if not all milestones are completed by the
report submission deadline but a full schedule through testing must be planned.
4) Testing Plan (10 points):
 Detail testing objectives, schedules, and check-lists for flight tests. If any testing has
been completed document the results of those tests. Although it is not necessary to
complete testing prior to the report submission deadline, a full testing plan must be
submitted.
Design Report Electronic Copy:
Each team must provide an electronic copy of their final design used for the report judging as
outlined below.
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Electronic copy must be RECEIVED by the deadline mentioned above.
Electronic report files must be named: “2016_NWDC_[school]_[team name].PDF”
Electronic report must be a single file with all figures/drawings included in the proper
report sequence in PDF format. (Free PDF file conversion programs are available on the
Internet, such as www.pdf995.com.)
Electronic reports should have all figures compressed to print resolution to minimize file
size.
Electronic reports must be less than 20 MB in size (including encoding for e-mail
transmission) and e-mailed to:
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2015 WING DESIGN COMPETITION
17
Appendix A: Airfoil Ordinates
The tables below list the ordinates from which the airfoils can be manufactured. Each
value is given as a percentage of the chord length. To get the actual dimension just
multiply each number by the desired chord length.
Table 2: E423 Airfoil Ordinates
Table 1: E422 Airfoil Ordinates
Chord Position
0.00002000
0.00033000
0.00071000
0.00125000
0.00157000
0.00194000
0.00237000
0.00288000
0.00348000
0.00415000
0.00571000
0.00751000
0.01065000
0.01365000
0.02892000
0.04947000
0.07533000
0.10670000
0.14385000
0.18727000
0.23688000
0.29196000
0.35163000
0.41449000
0.47867000
0.54275000
0.60579000
0.66690000
0.72503000
0.77912000
0.82836000
0.87219000
0.91012000
0.94179000
0.96692000
0.98519000
0.99629000
1.00000000
Lower Half
0.00088000
-0.00192000
-0.00362000
-0.00518000
-0.00590000
-0.00656000
-0.00717000
-0.00771000
-0.00823000
-0.00874000
-0.00969000
-0.01057000
-0.01177000
-0.01266000
-0.01485000
-0.01482000
-0.01236000
-0.00740000
-0.00002000
0.00922000
0.01913000
0.02865000
0.03687000
0.04283000
0.04626000
0.04760000
0.04715000
0.04501000
0.04126000
0.03625000
0.03050000
0.02444000
0.01844000
0.01286000
0.00794000
0.00390000
0.00106000
0.00000000
Chord Position
0.00002000
0.00071000
0.00481000
0.01262000
0.02421000
0.03953000
0.05852000
0.08106000
0.10700000
0.13611000
0.16816000
0.20286000
0.23987000
0.27885000
0.31947000
0.36149000
0.40464000
0.44870000
0.49347000
0.53893000
0.58491000
0.63092000
0.67644000
0.72090000
0.76373000
0.80436000
0.84221000
0.87671000
0.90734000
0.93358000
0.95530000
0.97304000
0.98706000
0.99655000
1.00000000
Upper Half
0.00088000
0.00879000
0.02093000
0.03419000
0.04812000
0.06232000
0.07646000
0.09023000
0.10337000
0.11562000
0.12676000
0.13657000
0.14485000
0.15138000
0.15590000
0.15824000
0.15828000
0.15593000
0.15116000
0.14410000
0.13524000
0.12506000
0.11391000
0.10215000
0.09010000
0.07803000
0.06620000
0.05481000
0.04400000
0.03376000
0.02381000
0.01434000
0.00650000
0.00159000
0.00000000
Chord Position
0.00002000
0.00033000
0.00071000
0.00125000
0.00157000
0.00194000
0.00237000
0.00288000
0.00348000
0.00415000
0.00571000
0.00751000
0.01065000
0.01365000
0.02892000
0.04947000
0.07533000
0.10670000
0.14385000
0.18727000
0.23688000
0.29196000
0.35163000
0.41449000
0.47867000
0.54275000
0.60579000
0.66690000
0.72503000
0.77912000
0.82836000
0.87219000
0.91012000
0.94179000
0.96692000
0.98519000
0.99629000
1.00000000
2015 WING DESIGN COMPETITION
Lower Half
0.00088000
-0.00192000
-0.00362000
-0.00518000
-0.00590000
-0.00656000
-0.00717000
-0.00771000
-0.00823000
-0.00874000
-0.00969000
-0.01057000
-0.01177000
-0.01266000
-0.01485000
-0.01482000
-0.01236000
-0.00740000
-0.00002000
0.00922000
0.01913000
0.02865000
0.03687000
0.04283000
0.04626000
0.04760000
0.04715000
0.04501000
0.04126000
0.03625000
0.03050000
0.02444000
0.01844000
0.01286000
0.00794000
0.00390000
0.00106000
0.00000000
Chord Position
0.00002000
0.00071000
0.00481000
0.01262000
0.02421000
0.03953000
0.05852000
0.08106000
0.10700000
0.13611000
0.16816000
0.20286000
0.23987000
0.27885000
0.31947000
0.36149000
0.40464000
0.44870000
0.49347000
0.53893000
0.58491000
0.63092000
0.67644000
0.72090000
0.76373000
0.80436000
0.84221000
0.87671000
0.90734000
0.93358000
0.95530000
0.97304000
0.98706000
0.99655000
1.00000000
Upper Half
0.00088000
0.00879000
0.02093000
0.03419000
0.04812000
0.06232000
0.07646000
0.09023000
0.10337000
0.11562000
0.12676000
0.13657000
0.14485000
0.15138000
0.15590000
0.15824000
0.15828000
0.15593000
0.15116000
0.14410000
0.13524000
0.12506000
0.11391000
0.10215000
0.09010000
0.07803000
0.06620000
0.05481000
0.04400000
0.03376000
0.02381000
0.01434000
0.00650000
0.00159000
0.00000000
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Table 3: MH114 Airfoil Ordinates
Chord Position
0.00000128
0.00015578
0.00047748
0.00102029
0.00188207
0.00307710
0.00536346
0.00818256
0.01396759
0.02998040
0.05146211
0.07820223
0.10998679
0.14654017
0.18753106
0.23256226
0.28117044
0.33282653
0.38695746
0.44295096
0.50015235
0.55787098
0.61535885
0.67182118
0.72640660
0.77822736
0.82641818
0.87014991
0.90865700
0.94123377
0.96708092
0.98551223
0.99640825
1.00000000
Lower Half
0.00020630
-0.00218399
-0.00360344
-0.00482311
-0.00589101
-0.00690420
-0.00833777
-0.00966916
-0.01167125
-0.01489783
-0.01693984
-0.01780217
-0.01752983
-0.01622017
-0.01399145
-0.01100035
-0.00741551
-0.00342225
0.00080409
0.00506331
0.00915869
0.01286723
0.01597279
0.01826471
0.01957527
0.01980849
0.01896858
0.01711775
0.01440675
0.01098584
0.00711905
0.00347938
0.00091297
0.00000000
Chord Position
0.00000128
0.00021738
0.00139717
0.00665698
0.01580501
0.02883347
0.04568918
0.06629112
0.09051427
0.11819963
0.14914254
0.18310506
0.21984312
0.25910372
0.30058729
0.34396060
0.38885365
0.43486602
0.48159244
0.52862389
0.57556669
0.62204386
0.66769773
0.71219794
0.75515297
0.79610663
0.83458560
0.87010598
0.90217220
0.93028455
0.95394941
0.97294285
0.98731466
0.99667566
1.00000000
Upper Half
0.00020630
0.00285253
0.00777183
0.01863245
0.03047906
0.04280482
0.05520889
0.06735503
0.07895233
0.08974616
0.09951468
0.10804821
0.11515990
0.12072122
0.12465754
0.12692343
0.12751147
0.12642440
0.12368504
0.11933627
0.11344647
0.10612640
0.09753021
0.08789714
0.07756051
0.06685087
0.05609031
0.04559033
0.03564269
0.02649819
0.01828860
0.01102133
0.00508030
0.00127091
0.00000000
Table 4: NACA 62(1)-212 Airfoil Ordinates
Chord Position
0.00000000
0.00577000
0.00836000
0.01346000
0.02609000
0.05122000
0.07627000
0.10127000
0.15121000
0.20110000
0.25094000
0.30077000
0.35058000
0.40039000
0.45019000
0.50000000
0.54983000
0.59968000
0.64957000
0.69950000
0.74947000
0.79948000
0.84955000
0.89967000
0.94983000
1.00000000
2015 WING DESIGN COMPETITION
Lower Half
0.00000000
-0.00870000
-0.01036000
-0.01277000
-0.01686000
-0.02287000
-0.02745000
-0.03128000
-0.03727000
-0.04178000
-0.04510000
-0.04743000
-0.04882000
-0.04926000
-0.04854000
-0.04654000
-0.04317000
-0.03872000
-0.03351000
-0.02771000
-0.02164000
-0.01548000
-0.00956000
-0.00429000
-0.00040000
0.00000000
Chord Position
0.00000000
0.00423000
0.00664000
0.01154000
0.02391000
0.04878000
0.07373000
0.09873000
0.14879000
0.19890000
0.24906000
0.29923000
0.34942000
0.39961000
0.44981000
0.50000000
0.55017000
0.60032000
0.65043000
0.70050000
0.75053000
0.80052000
0.85045000
0.90033000
0.95017000
1.00000000
Upper Half
0.00000000
0.00970000
0.01176000
0.01491000
0.02058000
0.02919000
0.03593000
0.04162000
0.05073000
0.05770000
0.06300000
0.06687000
0.06942000
0.07068000
0.07044000
0.06860000
0.06507000
0.06014000
0.05411000
0.04715000
0.03954000
0.03140000
0.02302000
0.01463000
0.00672000
0.00000000
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Table 5: SD 7043 Airfoil Ordinates
Chord Position
0.00052000
0.00555000
0.01669000
0.03324000
0.05501000
0.08183000
0.11345000
0.14956000
0.18979000
0.23374000
0.28094000
0.33088000
0.38302000
0.43678000
0.49153000
0.54665000
0.60146000
0.65530000
0.70751000
0.75740000
0.80430000
0.84755000
0.88650000
0.92047000
0.94881000
0.97110000
0.98713000
0.99678000
1.00000000
Lower Half
-0.00278000
-0.00770000
-0.01150000
-0.01452000
-0.01669000
-0.01802000
-0.01856000
-0.01839000
-0.01756000
-0.01617000
-0.01429000
-0.01204000
-0.00951000
-0.00683000
-0.00412000
-0.00148000
0.00096000
0.00311000
0.00487000
0.00615000
0.00688000
0.00703000
0.00654000
0.00546000
0.00400000
0.00248000
0.00119000
0.00031000
0.00000000
Chord Position
0.00052000
0.00083000
0.00509000
0.01334000
0.02581000
0.04249000
0.06331000
0.08821000
0.11702000
0.14954000
0.18549000
0.22457000
0.26639000
0.31056000
0.35665000
0.40422000
0.45282000
0.50199000
0.55127000
0.60019000
0.64825000
0.69500000
0.74004000
0.78301000
0.82351000
0.86108000
0.89522000
0.92544000
0.95121000
0.97202000
0.98736000
0.99681000
1.00000000
Table 6: USA-35B Airfoil Ordinates
Upper Half
-0.00278000
0.00404000
0.01236000
0.02106000
0.02975000
0.03818000
0.04612000
0.05340000
0.05989000
0.06549000
0.07015000
0.07382000
0.07645000
0.07802000
0.07850000
0.07789000
0.07620000
0.07347000
0.06975000
0.06515000
0.05974000
0.05362000
0.04690000
0.03979000
0.03256000
0.02553000
0.01897000
0.01315000
0.00828000
0.00451000
0.00191000
0.00046000
0.00000000
Chord Position
-0.00008000
0.00028000
0.00118000
0.00261000
0.00459000
0.00715000
0.01036000
0.01432000
0.01917000
0.02511000
0.03237000
0.04130000
0.05224000
0.06597000
0.08386000
0.10635000
0.13149000
0.15716000
0.18343000
0.21088000
0.23921000
0.26781000
0.29632000
0.32471000
0.35312000
0.38163000
0.41023000
0.43885000
0.46742000
0.49591000
0.52430000
0.55262000
0.58091000
0.60923000
0.63766000
0.66623000
0.69491000
0.72359000
0.75216000
0.78056000
0.80881000
0.83698000
0.86512000
0.89318000
0.92099000
0.94739000
0.97031000
0.98923000
1.00000000
Lower Half
0.00120000
-0.00173000
-0.00466000
-0.00759000
-0.01048000
-0.01330000
-0.01595000
-0.01823000
-0.01997000
-0.02132000
-0.02261000
-0.02387000
-0.02499000
-0.02584000
-0.02648000
-0.02705000
-0.02749000
-0.02758000
-0.02726000
-0.02685000
-0.02655000
-0.02633000
-0.02613000
-0.02588000
-0.02558000
-0.02524000
-0.02486000
-0.02447000
-0.02409000
-0.02374000
-0.02347000
-0.02326000
-0.02314000
-0.02310000
-0.02314000
-0.02324000
-0.02338000
-0.02352000
-0.02368000
-0.02390000
-0.02421000
-0.02460000
-0.02504000
-0.02549000
-0.02592000
-0.02635000
-0.02683000
-0.02730000
-0.02760000
Chord Position
-0.00008000
0.00010000
0.00080000
0.00201000
0.00378000
0.00616000
0.00927000
0.01319000
0.01801000
0.02392000
0.03126000
0.04053000
0.05214000
0.06570000
0.08075000
0.09812000
0.11849000
0.14084000
0.16387000
0.18721000
0.21091000
0.23516000
0.26011000
0.28574000
0.31185000
0.33805000
0.36407000
0.38984000
0.41549000
0.44128000
0.46742000
0.49402000
0.52110000
0.54858000
0.57633000
0.60417000
0.63191000
0.65938000
0.68654000
0.71342000
0.74013000
0.76682000
0.79368000
0.82090000
0.84859000
0.87649000
0.90385000
0.92963000
0.95276000
0.97276000
0.98989000
1.00000000
Upper Half
0.00120000
0.00416000
0.00717000
0.01029000
0.01355000
0.01698000
0.02065000
0.02454000
0.02858000
0.03279000
0.03741000
0.04267000
0.04867000
0.05507000
0.06100000
0.06638000
0.07157000
0.07630000
0.08035000
0.08370000
0.08629000
0.08814000
0.08932000
0.08990000
0.08998000
0.08959000
0.08870000
0.08730000
0.08536000
0.08288000
0.07992000
0.07651000
0.07273000
0.06864000
0.06431000
0.05982000
0.05524000
0.05055000
0.04570000
0.04064000
0.03534000
0.02980000
0.02400000
0.01792000
0.01158000
0.00509000
-0.00130000
-0.00742000
-0.01334000
-0.01900000
-0.02429000
-0.02760000
Appendices B through G give the aerodynamic performance for each airfoil as well as an outline
of the shape of the airfoil. All aerodynamic characteristics were calculated using computer
software designed for low Reynolds number calculations.
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Appendix B: Eppler 422 Airfoil Characteristics
Figure 4: E422 Airfoil
Figure 5: E422 Drag Polar
Figure 6: E422 Lift Curve
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Figure 7: E422 Moment Coefficient
Figure 8: E422 Lift/Drag Ratio
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Appendix C: Eppler 423 Airfoil Characteristics
Figure 9: E423 Airfoil
Figure 10: E423 Drag Polar
Figure 11: E423 Lift Curve
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Figure 12: E423 Moment Coefficient
Figure 13: E423 Lift/Drag Ratio
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Appendix D: Martin Hepperle 114 Airfoil Characteristics
Figure 14: MH 114 Airfoil
Figure 15: MH 114 Drag Polar
Figure 16: MH 114 Lift Curve
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Figure 17: MH 114 Moment Coefficient
Figure 18: MH 114 Lift/Drag Ratio
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Appendix E: NACA 62(1)-212 Airfoil Characteristics
Figure 19: NACA 62(1)-212 Airfoil
Figure 20: NACA 62(1)-212 Drag Polar
Figure 21: NACA 62(1)-212 Lift Curve
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Figure 22: NACA 62(1)-212 Moment Coefficient
Figure 23: NACA 62(1)-212 Lift/Drag Ratio
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Appendix F: Selig/Donovan 7043 Airfoil Characteristics
Figure 24: SD 7043 Airfoil
Figure 25: SD 7043 Drag Polar
Figure 26: SD 7043 Lift Curve
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Figure 27: SD 7043 Moment Coefficient
Figure 28: SD 7043Lift/Drag Ratio
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Appendix G: USA-35B Airfoil Characteristics
Figure 29: USA-35BAirfoil
Figure 30: USA-35BDrag Polar
Figure 31: USA-35BLift Curve
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Figure 32: USA-35BMoment Coefficient
Figure 33: USA-35BLift/Drag Ratio
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