Measurement and mapping of aerodynamic heating using a remote infrared scanning camera in continuous flow wind tunnels

Boylan, D. E.; Carver, D B; Stallings, D W; Trimmer, L. L.

doi:10.2514/6.1978-799

Cited by 19 publications

(4 citation statements)

References 2 publications

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“…To assess the accuracy of the technique, calibration procedures were developed; the repeatability of the measurements was evaluated; and a measurement error model was implemented. 32 ' 33 The results were confirmed also by other experimental means and were found to agree well with theoretical predictions. On the negative side, it was found that step changes in the temperature distribution could not be resolved, the response being blurred and smeared over a few adjacent pixels.…”

Section: Supersonic and Hypersonic Studiessupporting

confidence: 91%

Twenty-five years of aerodynamic research with infrared imaging

Gartenberg

Roberts

1992

Journal of Aircraft

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Section: Supersonic and Hypersonic Studiessupporting

confidence: 91%

Twenty-five years of aerodynamic research with infrared imaging

Gartenberg

Roberts

1992

Journal of Aircraft

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“…In the equation (2), through solving the equation through heat transfer coefficient h against these five parameters Tw、Taw、 Ti、(Cpk) 1/2 、t , and using the Taylor series method, one can get the random uncertain degree of the heat transfer coefficient [6] :…”

Section: Other Way To Raise Accuracy Of Heat Transfer Rates Measurementmentioning

confidence: 99%

Key Technical Study of Infrared Thermography on Aerodynamic Heating Measurement in Hypersonic Wind Tunnel

Li¹,

Zhiwei²,

Li³

2012

Proceedings of the 2012 International Conference on Quantitative InfraRed Thermography

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Abstract:In the article, it was discussed how to correct surface directional emittance in a big optical incident angle and how to relate model coordinates to corresponding pixel locations of model infrared mapping and how to raise the accuracy of heat transfer rates measurement. Some simple practical methods were obtained. As the example of these methods to be applied , the transfer rates on a thin skin flat plate with a wedge and on sphere-cylinder model were measured by means of infrared thermography or thermocouple. The infrared results and thermocouple ones agreed with each other very well.

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“…The energy detected from a known area on the surface (spot) is digitized and converted to an average surface temperature using known radiation laws. 3 In the phase change paint technique the model is sprayed with a paint containing a fine emulsion of wax having a known melting point. As the model heats up in the tunnel flow the wax melts wherever the surface temperature reaches the melting point.…”

Section: Test Programmentioning

confidence: 99%

MX Missile Thermal Mapping and Surface Flow Results

Maegley¹,

Carroll²

1982

Journal of Spacecraft and Rockets

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Results of wind tunnel tests to determine aerodynamic heating patterns and general flowfield characteristics on the MX missile are discussed. 5% and l2 l /2% scale models of the missile configuration were tested at Mach 6 and 8. Infrared scanning and phase change paint thermal mapping techniques were used to determine smooth wall turbulent and laminar heating levels and localized heating effects due to protuberances. Protuberances included a scaled raceway, lateral support pad shear tabs, and stage II roll control jets. The flowfield about the missile during the stage I/stage II separation event was investigated using a cold gas simulation of the stage II motor plume. Measured smooth wall heating rates confirmed both laminar and turbulent theoretical predictions and significant heating augmentation in excess of five times the smooth wall values was found in the vicinity of the leading edge of the raceway and the shear tabs. An extensive interaction region was produced by the roll control system jets. Schlieren photography of the staging event showed plume induced flow separation extending to the nose of the missile. NomenclatureA = area A ref = missile reference area D m = missile or model cross-sectional diameter h = heat-transfer coefficient (see Eq. 1), Btu/ft 2 -s-°R hi/hu = ratio of interference heating to undisturbed heating i.r. = infrared camera view £ = model or missile length M = Mach number p = static pressure P t = tunnel total pressure q -convective heat-transfer rate q = dynamic pressure RCS = roll control system Re? = freestream Reynolds number based on missile or model length Re/ft = unit freestream Reynolds number S = stage separation distance T r = recovery temperature T t = tunnel total temperature T w = model wall (surface) temperature a = model angle of attack 7 = ratio of specific heats Subscripts e = stage II nozzle exit £ = local external flow over missile or based on model/missile length oo = undisturbed freestream

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Measurement and mapping of aerodynamic heating using a remote infrared scanning camera in continuous flow wind tunnels

Cited by 19 publications

References 2 publications

Twenty-five years of aerodynamic research with infrared imaging

Twenty-five years of aerodynamic research with infrared imaging

Key Technical Study of Infrared Thermography on Aerodynamic Heating Measurement in Hypersonic Wind Tunnel

MX Missile Thermal Mapping and Surface Flow Results

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