Stagnation point heat transfer measurements in partially ionized air

Rose, P. H.; Stankevics, J. O.

doi:10.2514/3.2169

Cited by 49 publications

(14 citation statements)

References 24 publications

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“…The computational results are validated with experimental observations reported by Lobb [30], Rose et al [31] and Hornung [32] for the shock standoff distance and surface heat transfer distributions. Results of the current numerical simulations are validated with the shock tunnel data presented in Table 2.…”

Section: Condition Of Numerical Simulationsupporting

confidence: 77%

“…The first case study involves Lobb's experiment [30] devoted to the measure of shock detachment at 5.28 km/s. The second computation is also validated with the shock tube measurements of stagnation point heat flux for blunt bodies at 5.74 km/s from the work of Rose et al [31]. The RAM-CII flight is a program conducted by the NASA Langley Research Center to assess the effects of black-out during re-entry.…”

Section: Condition Of Numerical Simulationmentioning

confidence: 92%

“…As expected, the higher values of Q w are obtained with slower kinetics. The stagnation point heat transfer are reported in Table 4 and compared with experimental data [31]. Computed stagnation heat flux is over predicted with Gardiner, Moss and modified Dunn and Kang models.…”

Section: Rose and Stankevics's Experimentsmentioning

confidence: 99%

“…Figure 17 reflects the subtle differences that can be achieved between two kinetics (slow or fast) at thermal equilibrium. [35] 45.0 Experiment-Rose et al [31] 46.0 …”

Section: Interaction Of Type Ivr Around a Double-wedge In Hypersonic mentioning

confidence: 99%

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Physico - Chemical Modelling in Nonequilibrium Hypersonic Flow Around Blunt Bodies

Tchuen¹,

Burtschell²

2011

Aeronautics and Astronautics

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Section: Condition Of Numerical Simulationsupporting

confidence: 77%

Section: Condition Of Numerical Simulationmentioning

confidence: 92%

Section: Rose and Stankevics's Experimentsmentioning

confidence: 99%

“…Figure 17 reflects the subtle differences that can be achieved between two kinetics (slow or fast) at thermal equilibrium. [35] 45.0 Experiment-Rose et al [31] 46.0 …”

Section: Interaction Of Type Ivr Around a Double-wedge In Hypersonic mentioning

confidence: 99%

See 2 more Smart Citations

Physico - Chemical Modelling in Nonequilibrium Hypersonic Flow Around Blunt Bodies

Tchuen¹,

Burtschell²

2011

Aeronautics and Astronautics

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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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