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

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

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

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