NASA Langley Aerothermodynamics Laboratory: Hypersonic Testing Capabilities

Berger, Karen T.; Hollingsworth, Kevin E.; Wright, Shelia A.; Rufer, Shann J.

doi:10.2514/6.2015-1337

Cited by 49 publications

(13 citation statements)

References 21 publications

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“…Each of these facilities uses heated, dried, and filtered air as the test gas and provides for a variety of free-stream Reynolds numbers at free-stream Mach numbers of either 6 or 10. Berger et al 3 provides a detailed description of these facilities.…”

Section: Facilitiesmentioning

confidence: 99%

“…This data set was acquired in the 20-Inch Mach 6 Tunnel to compare with Hypersonic Thermodynamic Infrared Measurements (HYTHIRM) data from a boundary layer transition flight experiment on the Space Shuttle. 3 The temperatures on the windward surface of this model should be uniform and close to room temperature in the pre-run image taken under vacuum prior to flow through the tunnel.…”

Section: A Diagnostic Toolmentioning

confidence: 99%

“…(3). Therefore, only the initial temperatures and the temperatures at some subsequent time during the run are needed to compute heat transfer coefficients (c h ) at the surface of the model at that instant (t).…”

Section: Phosphor Thermography Systemmentioning

confidence: 99%

“…3 This calibration, which is derived for each new batch of the phosphor mixture, uses the red and green components of the image to construct a lookup table that converts the intensities to a temperature value. Currently, this calibration is valid over a temperature range from 65°F to 320°F.…”

Section: Phosphor Thermography Systemmentioning

confidence: 99%

“…The IHEAT program upgrade is one part of several modifications and calibrations that recently have been performed to improve the capabilities of and the data acquired from the LAL facilities. 3 Examples of previous studies that used the phosphor thermography capability are provided in Refs. 4-20.…”

Section: Introductionmentioning

confidence: 99%

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Features of the Upgraded Imaging for Hypersonic Experimental Aeroheating Testing (IHEAT) Software

Mason

Rufer

2016

32nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference

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The Imaging for Hypersonic Experimental Aeroheating Testing (IHEAT) software is used at the NASA Langley Research Center to analyze global aeroheating data on wind tunnel models tested in the Langley Aerothermodynamics Laboratory. One-dimensional, semi-infinite heating data derived from IHEAT are used in the design of thermal protection systems for hypersonic vehicles that are exposed to severe aeroheating loads, such as reentry vehicles during descent and landing procedures. This software program originally was written in the PV-WAVE ® programming language to analyze phosphor thermography data from the two-color, relative-intensity system developed at Langley. To increase the efficiency, functionality, and reliability of IHEAT, the program was migrated to MATLAB ® syntax and compiled as a stand-alone executable file labeled version 4.0. New features of IHEAT 4.0 include the options to perform diagnostic checks of the accuracy of the acquired data during a wind tunnel test, to extract data along a specified multi-segment line following a feature such as a leading edge or a streamline, and to batch process all of the temporal frame data from a wind tunnel run. Results from IHEAT 4.0 were compared on a pixel level to the output images from the legacy software to validate the program. The absolute differences between the heat transfer data output from the two programs were on the order of 10 -5 to 10 -7 . IHEAT 4.0 replaces the PV-WAVE ® version as the production software for aeroheating experiments conducted in the hypersonic facilities at NASA Langley. Nomenclature β = thermal product, = ! (Btu/ft 2 -°R-s 1/2 ) C = sub-expression from step function equation, ! ℎ ! ! c h = convective heat transfer coefficient (lb/ft 2 -s) c P = specific heat capacity at constant pressure (Btu/lb-°F) D = sub-expression from step function equation, ℎ !" ! ℎ ! − !"!# h = enthalpy (Btu/lb) k = thermal conductivity (Btu/hr-ft-°F) κ = thermal diffusivity (ft 2 /s) L = characteristic length of model in axial direction (in.) = sub-expression from step function equation, P = pressure (psi or psia) = rate of heat transfer (Btu/hr-ft 2 ) ρ = density (slug/ft 3 ) t = time (s) T = temperature (°F or °R) θ = temperature difference (°F or °R) x = axial dimension on the model (in.) y = longitudinal dimension on the model (in.) y ref = characteristic length of model in longitudinal direction (in.)2 Subscripts: aw = adiabatic wall conv = convection F-R = Fay-Riddell init = initial tw = tunnel wall w = wall (surface of model) Acronyms: IHEAT = Imaging for Hypersonic Experimental Aeroheating Testing IR = infrared LAL = Langley Aerothermodynamics Laboratory 1D = one-dimensional 2D = two-dimensional 3D = three-dimensional

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Section: Facilitiesmentioning

confidence: 99%

Section: A Diagnostic Toolmentioning

confidence: 99%

Section: Phosphor Thermography Systemmentioning

confidence: 99%

Section: Phosphor Thermography Systemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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