Hypersonic aerodynamic/aerothermodynamic testing capabilities at Langley Research Center - Aerothermodynamic Facilities Complex

A series of aerodynamic heating tests was conducted on a 70-deg sphere-cone planetary entry vehicle model in a Mach 10 perfect-gas wind tunnel at freestream Reynolds numbers based on diameter of 8.23x10 4 to 3.15x10 5 . Surface heating distributions were determined from temperature time-histories measured on the model and on its support sting using thin-film resistance gages. The experimental heating data were compared to computations made using an axisymmetric/2D, laminar, perfect-gas Navier-Stokes solver. Agreement between computational and experimental heating distributions to within, or slightly greater than, the experimental uncertainty was obtained on the forebody and afterbody of the entry vehicle as well as on the sting upstream of the free-shear-layer reattachment point. However, the distributions began to diverge near the reattachment point, with the experimental heating becoming increasingly greater than the computed heating with distance downstream from the reattachment point. It was concluded that this divergence was due to transition of the wake free shear layer just upstream of the reattachment point on the sting. Nomenclature B C,Hheating bias error

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“…Aerothermodynamic testing was conducted in the NASA Langley Research Center (LaRC) 31-Inch Mach 10 Air Tunnel 16 (Fig. 3).…”

Section: Facility Descriptionmentioning

confidence: 99%

Transition effects on heating in the wake of a blunt body

Hollis

Perkins

1997

32nd Thermophysics Conference

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“…Over the past decade, numerous experimental and numerical study of temperature and heat flow on aircraft elements were conducted to estimate and improve methods and models which are used for a prediction of operating conditions of the hypersonic vehicle [3][4][5].…”

Section: Introductionmentioning

confidence: 99%

Application of the Deconvolution Methods for Processing of Measurement Signals in the Fast Processes

Goldfeld¹,

Pickalov²

2016

Proceedings of the VII European Congress on Computational Methods in Applied Sciences and Engineering (ECCOMAS Congress 2016)

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“…CF 4 = fluoromethane (test gas used in the Langley Research Center 20-Inch Hypersonic CF 4 Tunnel) Kn L = freestream Knudsen number based on vehicle length L = Body length parameter M 1 = freestream Mach number P T, 1 = stagnation pressure P T, 2 = post-normal-shock stagnation pressure, or pitot pressure Re L = freestream Reynolds number based on vehicle length Re 1 = unit freestream Reynolds number γ = ratio of specific heats…”

Section: Nomenclaturementioning

confidence: 99%

“…These tests were run in the Langley Aerothermodynamics Laboratory (LAL) 20-Inch Hypersonic CF 4 Tunnel and 31-Inch Mach 10 Air Tunnel. A complete description of these facilities is given by Micol.…”

Section: Hypersonic Wind-tunnel Test Facilitiesmentioning

confidence: 99%

Testing of Flexible Ballutes in Hypersonic Wind Tunnels for Planetary Aerocapture

Buck

2006

44th AIAA Aerospace Sciences Meeting and Exhibit

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Studies were conducted for the In-Space Propulsion (ISP) Ultralightweight Ballute Technology Development Program to increase the technical readiness level of inflatable decelerator systems for planetary aerocapture. The present experimental study was conducted to develop the capability for testing lightweight, flexible materials in hypersonic facilities. The primary objectives were to evaluate advanced polymer film materials in a high-temperature, high-speed flow environment and provide experimental data for comparisons with fluid-structure interaction modeling tools. Experimental testing was conducted in the Langley Aerothermodynamics Laboratory 20-Inch Hypersonic CF 4 and 31-Inch Mach 10 Air blowdown wind tunnels. Quantitative flexure measurements were made for 60 degree half angle afterbody-attached ballutes, in which polyimide films (1-mil and 3-mil thick) were clamped between a 1/2-inch diameter disk and a base ring (4-inch and 6-inch diameters). Deflection measurements were made using a parallel light silhouette of the film surface through an existing schlieren optical system. The purpose of this paper is to discuss these results as well as free-flying testing techniques being developed for both an afterbodyattached and trailing toroidal ballute configuration to determine dynamic fluid-structural stability. Methods for measuring polymer film temperature were also explored using both temperature sensitive paints (for up to 370 C) and laser-etched thin-film gages.

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Hypersonic aerodynamic/aerothermodynamic testing capabilities at Langley Research Center - Aerothermodynamic Facilities Complex

Cited by 48 publications

References 0 publications

Transition effects on heating in the wake of a blunt body

Transition effects on heating in the wake of a blunt body

Application of the Deconvolution Methods for Processing of Measurement Signals in the Fast Processes

Testing of Flexible Ballutes in Hypersonic Wind Tunnels for Planetary Aerocapture

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