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Experimental Study of Convective Heating on the Back Face and Payload of a Hypersonic Inflatable Aerodynamic Decelerator (HIAD) AeroshellA wind tunnel test program has been conducted to define convective heating environments on the back-face of a Hypersonic Inflatable Aerodynamic Decelerator aeroshell. Wind tunnel testing was conducted at Mach 6 and Mach 10 at unit Reynolds numbers from 0.5×10(exp 6)/ft to 3.9×10(exp 6)/ft on a 6.3088 in diameter aeroshell model. Global heating data were obtained through phosphor thermography on the aeroshell back face, as well as on the payload and the aeroshell front face. For all test conditions, laminar flow was produced on the aeroshell front face, while the separated wake shear layer and aeroshell back-face boundary layer were transitional or turbulent. Along the leeward centerline of the aeroshell back face and payload centerbody, heating levels increased with both free stream Reynolds number and angle of attack. The Reynolds number dependency was due to increasing strength of wake turbulence with Reynolds number. The angle-of-attack dependency was due to movement of the wake-vortex reattachment point on the aeroshell back face. The maximum heating levels on the aeroshell back face and payload were approximately 5% to 6%, respectively, of the aeroshell front-face stagnation point. To allow for extrapolation of the ground test data to flight conditions, the back face and payload heating levels were correlated as a function of aeroshell front-face peak momentum thickness Reynolds numbers.
Document ID
20170002597
Acquisition Source
Langley Research Center
Document Type
Technical Publication (TP)
Authors
Hollis, Brian R. (NASA Langley Research Center Hampton, VA, United States)
Berry, Scott A. (NASA Langley Research Center Hampton, VA, United States)
Hollingsworth, Kevin E. (Jacobs Technology, Inc. Hampton, VA, United States)
Wright, Sheila A. (Jacobs Technology, Inc. Hampton, VA, United States)
Date Acquired
March 28, 2017
Publication Date
March 1, 2017
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
L-20785
NASA-TP-2017-219581
NF1676L-20696
Report Number: L-20785
Report Number: NASA-TP-2017-219581
Report Number: NF1676L-20696
Funding Number(s)
WBS: WBS 630154.02.07
Distribution Limits
Public
Copyright
Public Use Permitted.

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