Stagnation Point Heat-Transfer Measurements in Dissociated Air

Rose, P. H.; Stark, W. I.

doi:10.2514/8.7519

Cited by 95 publications

(39 citation statements)

References 5 publications

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“…The theoretical solutions of Fay and Riddell have been verified by many experiments, such (14) as those of Rose and Stark.…”

Section: It Is Found Upon Evaluation Of Equation 25mentioning

confidence: 78%

Methods for Predicting Aerodynamic Heating Rates to High-Velocity Bodies in the Upper Atmosphere

Elliott¹

1966

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“…The theoretical solutions of Fay and Riddell have been verified by many experiments, such (14) as those of Rose and Stark.…”

Section: It Is Found Upon Evaluation Of Equation 25mentioning

confidence: 78%

Methods for Predicting Aerodynamic Heating Rates to High-Velocity Bodies in the Upper Atmosphere

Elliott¹

1966

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“…Figure 8 shows a number of numerical and experimental data from subsonic and hypersonic facilities where the slope corresponds to the parameter K in Eqs. (6) and (10) [22,[36][37][38][39][40][41][42].…”

Section: )mentioning

confidence: 99%

Hypersonic Aerothermochemistry Duplication in Ground Plasma Facilities: A Flight-to-Ground Approach

Sakraker

Turchi

Chazot

2015

Journal of Spacecraft and Rockets

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High conservative safety margins, applied to the design of spacecraft thermal protection systems for planetary entry, need to be reduced for higher efficiency of future space missions. Ground testing of such protection systems is of great importance during the design phase. This study covers a methodology for simulating the complex hypersonic entry aerothermochemistry in a plasma wind tunnel for a given spacecraft geometry without any assumption on axisymmetry or bluntness. A demonstration of this proposed methodology is made on the Qubesat for Aerothermodynamic Research and Measurements on AblatioN, QARMAN mission, which is a rectangular reentry CubeSat with a cork-based ablative thermal protection system in the front unit. The reacting boundary-layer profiles of the hypersonic entry probe compare well with the ones developing at the stagnation region of the plasma test model, defined with the proposed flight-to-ground duplication method.

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“…1.20). However, the transfer of hea -52 -in these experiments was measured by means of calorimeters which consist of platinum plates placed into the stream (see [49]). We can see The increase in pressure produced by the boundary layer can be * determined by assuming the boundary layer, having a thickness 6 szh' to have solidified.…”

mentioning

confidence: 99%

Aerodynamic and Radiation Heating During Flight

Drakin¹

1963

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Stagnation Point Heat-Transfer Measurements in Dissociated Air

Cited by 95 publications

References 5 publications

Methods for Predicting Aerodynamic Heating Rates to High-Velocity Bodies in the Upper Atmosphere

Methods for Predicting Aerodynamic Heating Rates to High-Velocity Bodies in the Upper Atmosphere

Hypersonic Aerothermochemistry Duplication in Ground Plasma Facilities: A Flight-to-Ground Approach

Aerodynamic and Radiation Heating During Flight

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