Force and heat transfer measurements in hypersonic free-jet flow

Legge, H.

doi:10.2514/6.1994-2633

Cited by 4 publications

(1 citation statement)

References 2 publications

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“…The first possible source of the disagreement between the CFD result and the PLIIF visualization is the Ashkenas and Sherman relations that provide the freestream conditions in the numerical simulations, which may not be appropriate for relatively large streamline angles greater than approximately 10 • . 25 Another possible cause of the disagreement between the numerical and experimental results is the interaction of the bow shock with the barrel shock in the experiments, which is shown in Figure 22. This interaction between the two shock structures in the experimental facility, referred to as the triple-point, can change the profile of the bow shock around the aeroshell.…”

Section: E Comparisons With Experimental Datamentioning

confidence: 97%

Aerodynamic Interactions of Reaction Control System Jets on Mars Entry Aeroshells

Alkandry

Boyd

Reed

et al. 2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The fluid interactions produced by a sonic reaction control system (RCS) thruster for a Mars-entry aeroshell are investigated using computational fluid dynamics (CFD). The study uses a scaled Mars Science Laboratory (MSL) aeroshell at a 20 • angle-of-attack in Mach 12 flow of I2-seeded N2 gas. The RCS jet is directed either parallel or transverse to the freestream flow in order to examine the effects of the thruster orientation with respect to the center of gravity of the aeroshell. The results show that both the parallel and transverse RCS jets obstruct the flow around the aeroshell and impinge on the surface, which increase the overall pressure on the aftbody. As a result, the RCS jet decreases both the drag and lift forces, and the moment acting on the aeroshell, particularly at relatively large RCS thrust conditions. The results also indicate that the fluid interactions produced by the parallel and transverse jets affect the control effectiveness of the RCS. The performance of the parallel RCS thruster is close to ideal due to relatively small aerodynamic interference induced by the jet. However, the relatively large aerodynamic interference produced by the transverse RCS jet causes a deficit of control authority. The physical accuracy of the computational method is assessed by comparing the numerical results with experimental visualizations.

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Section: E Comparisons With Experimental Datamentioning

confidence: 97%

Aerodynamic Interactions of Reaction Control System Jets on Mars Entry Aeroshells

Alkandry

Boyd

Reed

et al. 2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Aerodynamic Interactions of Reaction-Control-System Jets for Atmospheric Entry Aeroshells

Alkandry

Boyd²,

Reed

et al. 2013

AIAA Journal

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Comparative Similarity Analysis of Hypersonic Rarefied Gas Flows Near Simple-Shape Bodies

Riabov

1998

Journal of Spacecraft and Rockets

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Hypersonic viscous ows near simple-shape bodies (wedge, cone, disk, and plate) have been studied numerically under the conditions of wind-tunnel experiments with underexpanded jets. The direct simulation Monte Carlo technique has been used to study the in uence of similarity parameters on the ow structure near the bodies and on the aerodynamic coef cients in hypersonic streams of air, nitrogen, helium, and argon. It has been found that, for conditions approaching the hypersonic stabilization limit, the Reynolds number and temperature factor are primary similarity parameters. The in uence of other parameters (speci c heat ratio, viscosity-approximation parameter, and the Mach number) becomes signi cant at low Reynolds numbers (less than 10) and small values of the hypersonic similarity parameter (less than 1). The numerical results are in good agreement with experimental data, which were obtained in a vacuum chamber at low and moderate Reynolds numbers from 0.1 to 200. In the studies of the pitching moment and lift coef cients, a three-dimensional numerical approach should be used to simulate nonuniform ow near a plate, cone, and wedge under the experimental conditions with freejets.

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Force and heat transfer measurements in hypersonic free-jet flow

Cited by 4 publications

References 2 publications

Aerodynamic Interactions of Reaction Control System Jets on Mars Entry Aeroshells

Aerodynamic Interactions of Reaction Control System Jets on Mars Entry Aeroshells

Aerodynamic Interactions of Reaction-Control-System Jets for Atmospheric Entry Aeroshells

Comparative Similarity Analysis of Hypersonic Rarefied Gas Flows Near Simple-Shape Bodies

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