NASA Technical Reports Server (NTRS) 20170011246: Capabilities of the Unitary Plan Wind Tunnel

3.4 MB·English

by  NASA Technical Reports Server (NTRS)

NASA Ames Research Center
Capabilities of the Unitary Plan Wind Tunnel
Frank Kmak
Chief, Wind Tunnel Division
Ames Research Center
January 11, 2015
ARC Unitary Plan Wind Tunnel
NASA Ames Research Center
Wind Tunnel Division Facilities
High Pressure Air
Fluid Mechanics
(HPA) Storage
Laboratory (FML)
Tanks
High Pressure Air
High Pressure Air (HPA)
(HPA) Compressor Compressor C1D
C1A & HPA Control
Room
Unitary Plan
Wind Tunnel
(UPWT)
12-Ft PWT Model
Preparation Rooms
(MPR)
Balance
Calibration
Laboratory
12-Ft PWT
Mitsubishi Makeup
Air (MUA) Compressor
Compressor Blade Shop
Reynolds Number Range
11x11-Foot Transonic Wind Tunnel 9x7-Foot Supersonic Wind Tunnel
10.0!
9.0!
!
) 8.0!
t
o
o
f

r 7.0!
e
p

s
n
o 6.0!
Milli
(
r 5.0!
e
b
m
u 4.0!
N

s
d
ol 3.0!
n
y
e
R
2.0!
1.0!
0.0!
0.0! 0.5! 1.0! 1.5! 2.0! 2.5! 3.0!
Mach Number!
11-by 11-Foot Transonic Test Section
• Excellent Flow Quality
•Turbulence Reduction System
• Excellent optical access
• Wall interference correction system
• Sting mount and turntable model
supports
• Complete automation of tunnel and
model support operations
• Modern control room
• Slotted-wall test section (22’) with
baffles and 6% porosity
• 3-stage compressor and variable
camber inlet guide vanes
T11-0245/0255 - NASA ERA UHB
Powered Semi-span Test
OPERATING CHARACTERISTICS OF THE!
NASA AMES RESEARCH CENTER !
11-BY 11-FOOT TRANSONIC WIND TUNNEL!
12.0!
Stagnation Temperature = 560° R! Total!
Pressure!
11.0! (psfa)!
1900! 176 MW Power Limit!
1800!
10.0! Test Section ! 1700!
Dynamic Pressure! 1600!
q (psf)! 1500! 4608!
1400!
9.0! 1300! 4320!
)! Maximum! 1200!
t Operating! 1100!
o
fo 8.0! P4r6e0s8su pres!fa! 1000!

per 900! 3600!
800!
s 7.0!
n
o 700!
Milli 600!
( 6.0! 2880!
er 500!
b
m
u 5.0! 400!
N

s
d 300! 2160!
ol
n 4.0!
y
e
R 200!
3.0! 1440!
100!
2.0!
720!
1.0!
432!
Minimum Operating Pressure 432 psfa!
0.0!
0.0! 0.1! 0.2! 0.3! 0.4! 0.5! 0.6! 0.7! 0.8! 0.9! 1.0! 1.1! 1.2! 1.3! 1.4! 1.5!
Mach Number!
Lower limit of PES!
Source: Test 11-0051 IST Revised 2/2015
Sting Mounted Models in 11x11-Foot
Transonic Test Section
Semi-Span Models in 11x11-Foot
Transonic Test Section
PIV in the 11x11-Foot Transonic Test Section
T11-0247 NESC 120-CA CPAS
Comprehensive Study of the Flow Around a Simplified
Orion Capsule Model
• Wind-tunnel testing of Orion showed boundary-layer
state on heat shield significantly affected Crew Module
aerodynamics
• Agreement between CFD and experiments was poor
below ~M 0.8
• Study initiated by NASA Engineering and Safety
Center (NESC) to reduce uncertainty in Orion wake
flow
• Comprehensive measurement suite
– Particle Image Velocimetry (PIV)
– Pressure Sensitive Paint (PSP)
– Infrared (IR) thermography to locate transition and
separation lines
– Unsteady pressures around heat-shield shoulder
and in back shell
– Boundary-layer measurements at one location on
the heat shield
– High-speed shadowgraph videos (6,000 frames
per second)
11x11-Foot TWT Optical Access
PSP cameras
and lights
IR window
High-speed
PIV camera
IR window