AAE 520 Experimental Aerodynamics Aero & Space …...Purdue University - School of Aeronautics and...
Transcript of AAE 520 Experimental Aerodynamics Aero & Space …...Purdue University - School of Aeronautics and...
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Aero & Space Technology
Products & Services
Promoted by:
Resources International, Inc.895 Edgewater Drive, Lexington, KY 40502-3159, USA
https://riinc.net
Provided by:
AEOLUS AERO TECH Pvt. Ltd.Bengaluru, Karnataka, India
In collaboration with
Space TangoKentucky, USA
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Organization
AEOLUS AERO TECHBengaluru, India
Manufacture & Service
RESOURCES INTERNATIONAL, Inc.Kentucky, USA
Promotion & Distribution
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Aeolus Aero Tech (AAT)
202, 3rd Floor, Rajadathri Building
2nd Main Road, Kasturi Nagar
Bengaluru 560 043
Resources International, Inc., Lexington, KY, USA https://riinc.net
• Global Leader in Aerospace Products and Services
• Delivers affordable, High Technology Solutions
• Uncompromising Business Ethics & Delivery
• World class Technical Expertise & Collaboration
• Dedicated to Customer Satisfaction & Mission
• Assist with Manufacturing, Assembly and Testing
• Provide Life-time Engineering & Technical Support
• Champion Alternative Wind Energy (500 W to 5 KW)
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Aero-Space Products
Resources International, Inc., Lexington, KY, USA https://riinc.net
A. Educational Labs
B. Heat Pipes & Thermosyphons
C. Wind Tunnels
D. Space Tech Products
E. Micro-Gravity Research
F. CubeSat: Design, Develop & Deploy
G. Alternative Wind Energy (500 W–5 KW)
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
• Objective– Accurately simulate the fluid flow about atmospheric
vehicles
– Measure -Forces, moments, pressure, shear stress, heat
transfer, flowfield (velocity, pressure, vorticity,
temperature)
Wind Tunnels
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
U
Low Speed Vehicles - M<.3
Gallilean Transformation
Flight in atmosphere
Scale =L
Wind Tunnel - Model Scale =
Issues
Flow Quality - Uniformity and
Turbulence Level
Wind Tunnel Wall Interference
Reynolds Number Simulation
U
ULU
Re
Stationary Walls
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
History
Whirling Arm
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Eiffel Tunnel
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Wright Brothers
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
• Closed Return
• Open Return
• Double Return
• Annular Return
Wind Tunnel Layout
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Closed Return(open test section)
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Open Return
Closed Test Section
15 Hp. Dual
Centrifugal Blower
Exhaust
Exhaust
Louversfor SpeedAdjustment
Test Section
18 inch Diameter
25 to 1 ContractionScreens High Contraction Wind Tunnel
Top View
Diffuser
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Double Return
U N I V E R S I T Y OF W A S H I N G T O N
A E R O N A U T I C A L L A B O R A T O R Y
Kirsten Wind Tunnel
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Annular Wind
Tunnel
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
• Subsonic (< Mach 0.8)
• Transonic (Mach 0.8 ~ Mach 1.2)
• Supersonic (Mach 1.2 ~ Mach 5.0)
• Hypersonic (Mach 5.0 ~ Mach 10.0)
• Cryogenic (-150 0C ~ -180 0C)
• Specialty– Automobiles
– Environmental- Icing, Buildings, etc.
Types of Wind Tunnels
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Subsonic
Wind Tunnels
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
40’ x 80’ and 80’ x 120’
NASA Ames
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Fans for 40x80 and 80x120
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
40’x80’ 80’x120’
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
12 foot Pressure Tunnel
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
12-Foot Pressure Wind Tunnel: Specifications
Primary Use:
The facility is used primarily for high Reynolds number testing, including the development of high-lift
systems for commercial transports and military aircraft, high angle-of-attack testing of maneuvering
aircraft, and high Reynolds number research.
Capability:
Mach Number: 0-0.52
Reynolds Number per foot: 0.1 - 12X106
Stagnation Pressure, PSIA: 2.0 - 90
Temperature Range: 540 ° - 610 ° R
Closed circuit, single return, variable density, closed throat, wind tunnel with exceptionally low turbulence
Model-support systems available:
Strut with variable pitch and roll capability
High angle-of-attack turntable system
Dual-strut turntable mechanism for high-lift testing
Semispan mounting system
Internal strain-gage balances used for force and moment testing
Capability for measuring multiple fluctuating pressures
Temperature-controlled auxiliary high-pressure (3000 psi)
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Transonic
Wind Tunnels
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Transonic Wind Tunnels
Wall interference is a
severe problem for transonic
wind tunnels.
Flow can “choke”
Shock wave across the
tunnel test section
Two Solutions
Porous Walls
Movable Adaptive Walls
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
The 8x6/9x15 Complex at the NASA Lewis Research Center in Cleveland, Ohio is,
is unique in its dual capacity role as both a high-speed and low speed test facility.
8x6 Functions & CapabilitiesThe 8x6 Foot Supersonic Wind Tunnel provides customers with a Facility capable of testing large
scale aeropropulsion hardware:
In a continuous Mach 0-2.0 airstream
At varying Reynolds Numbers (3.6 - 4.8 x 106/ft) and altitude conditions (ambient to 38,000ft)
In either aerodynamic (closed) or Propulsion (open) cycle without exhaust scoops
Employing high data systems to support steady and transient data acquisition
Supported by a variety of systems including: Schlieren, infrared imaging, sheet lasers, LDV,
GH2 fuel, high pressure air, and hydraulics.
8x6 Characteristics & Performance
Test section size 8ft H, 6ft W, 23.5ft L
Mach number range 0 - 2.0
Relative altitude 1000 - 35000 ft
Dynamic Pressure 3.6 - 4.8 x 106/ft
Stagnation Pressure 15.3 - 25 psia
Temperature 60 - 250oF
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
8x6 at
NASA Lewis
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
9x15 at NASA Lewis
Back Leg of the 8x6
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
S1MA wind tunnel is equipped with two counter rotating fans, driven by
Pelton turbines, the power of which is 88 MW;
Mach number is continuously adjustable from 0.05 to 1 by varying the fan
speed from 25 to 212 rpm.
S1MA Wind Tunnel Atmospheric, closed-circuit, continuous
flow wind tunnel, from Mach 0.05 to Mach 1
Modane-Avrieux
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
16T at AEDC
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
S2Ma Wind Tunnel
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Supersonic
Wind Tunnels
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Hypersonic
Wind Tunnels
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
enables the testing of large hypersonic
airbreathing propulsion systems at flight
enthalpies from
Mach 4 to Mach 7.
The NASA Langley 8-
Foot High Temperature
Tunnel (8’ HTT)
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Cryogenic
Wind Tunnels
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
NATIONAL
TRANSONIC
FACILITY
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
The Cryogenic Ludwieg-Tube at Göttingen (KRG)
Adaptive wall test section
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Icing
Wind Tunnels
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Icing Tunnel
NASA Lewis Research Center
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Automobile
Wind Tunnels
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Wind Tunnel Power
Requirements
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Wind Tunnel Circuit Elements
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Closed Return Tunnel
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Turbulence Management System
Stilling Section - Low speed and uniform flow
Screens - Reduce Turbulence [Reduces Eddy size for Faster Decay]
- Used to obtain a uniform test section profile
- Provide a flow resistance for more stable fan operation
Honeycomb - Reduces Large Swirl Component of Incoming Flow
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
Corners
Abrupt Corner without Vanes 0.1
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
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Purdue University - School of Aeronautics and Astronautics
AAE 520 Experimental Aerodynamics
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