5 metre pressurised low-speed
wind tunnel
A high Reynolds number facility for the investigation
of flow physics and the prediction of full-scale
performance.
• Large size makes
accurate modelling of
details possible
• Pressurisation gives
simulation of full-scale
conditions for take-off
and landing of combat
aircraft
• Segregation of
compressibility and
scale effects permits
more accurate
prediction of full-scale
performance of large
transport aircraft
The tunnel fan
Landing and take-off performance is
of critical importance for both
military and civil aircraft. The 5m
pressurised low-speed wind tunnel
has a simulation capability that is
unique in the UK, and it provides
high quality data that is of great
value to the aerospace industry.
Civil aircraft testing
Aerial view of wind tunnel
Main characteristics and
performance
• Test section size: 5m x 4.2m
• Speed and Pressure Range:
Maximum Mach No 0.34
Maximum Pressure 3
atmospheres
• Drive Power: 12 MW continuous
• Turbulence level: u1 ≈ 0.08%
Test techniques and equipment
• Force-Measurements:
6-component underfloor balance
or internal strain-gauge balance.
• Pressure-Measurements:
Solid-state (EPS) multiple pressure
measurement.
• Flow-visualisation:
Fluorescent mini-tufts, surface oilflow, photographic wake imaging,
liquid crystals.
• Ground-plane Simulation:
False floor height remotely
Particle Image Velocimetry (PIV)
Picture taken during tests within
EEC EUROWAKE programme
controlled beneath fixed model.
• Particle Image Velocimetry (PIV):
Non-intrusive laser technique for
flowfield investigation.
• Balance Calibration Machine:
Computer controlled and capable
of applying maximum loads to
underfloor balances and straingauge balances.
• Data Acquisition:
On-line plots of processed
aerodynamic coefficients. Suite of
data-processing programmes to
suit customer requirements.
Model support and force measuring
system
• Interchangeable cart-mounted
models for rapid model changeovers.
• Two underfloor balances with
rotating turntable for either floormounted half-model, or full-model
on various strut supports.
• Rear sting support with range of
available 6-component straingauge balances. Alternative stings
with range of incidence up to 90°.
Roll units for model and for sting
to ± l80°.
• By permitting depressurisation of the
test section only, the 5m wind tunnel
enables rapid access for model
changes thereby allowing high
productivity. It is used for a wide
range of tests, including research
into the aerodynamics of high-lift
systems. helicopters, STOVL aircraft
and the development of wind-tunnel
techniques.
Helicopter testing
IT
For more information please contact:
Customer Contact Team
QinetiQ
Cody Technology Park
Ively Road
Farnborough
Hampshire
GU14 0LX
United Kingdom
Tel +44 (0) 8700 100942
www.QinetiQ.com
© Copyright QinetiQ ltd 2002
QINETIQ/FST/CAT/PUB013051