Blunt-Nose Inviscid Airflows With Coupled Nonequilibrium Processes

HALL, J. GORDEN; Eschenroeder, Alan Q.; Marrone, Paul V.

doi:10.2514/2.6906

Cited by 9 publications

(12 citation statements)

References 4 publications

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“…The first comprehensive nonequilibrium blunt-body analysis was carried out by Hall et al [186] in 1962, well before the advent of time-marching solutions. In [186], the analytical technique was an inverse solution-assuming a given shock shape, integrating the nonequilibrium flowfield downstream of the given shock, and finding the body shape that supports the given shock.…”

Section: Nonequilibrium Blunt-body Flowsmentioning

confidence: 99%

“…In [186], the analytical technique was an inverse solution-assuming a given shock shape, integrating the nonequilibrium flowfield downstream of the given shock, and finding the body shape that supports the given shock. Setting up a coordinate system where x and y are tangential and normal to the shock respectively, Hall et al replaced the partial derivatives in the x direction with a sevenpoint finite difference; hence, the x derivatives are known numbers, and the governing flow equations become ordinary differential equations in the y direction.…”

Section: Nonequilibrium Blunt-body Flowsmentioning

confidence: 99%

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Hypersonic and High-Temperature Gas Dynamics, Second Edition

Anderson¹

2006

970

603

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Data and information appearing in this book are for information purposes only. AIAA is not responsible for any injury or damage resulting from use or reliance, nor does AIAA warrant that use or reliance will be free from privately owned rights. Downloaded by Stanford University on September 30, 2012 | http://arc.aiaa.org | , for all their love and understanding Downloaded by Stanford University on September 30, 2012 | http://arc.aiaa.org |

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Section: Nonequilibrium Blunt-body Flowsmentioning

confidence: 99%

Section: Nonequilibrium Blunt-body Flowsmentioning

confidence: 99%

Hypersonic and High-Temperature Gas Dynamics, Second Edition

Anderson¹

2006

970

603

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“…For nonequilibrium flows, Lick applied inverse methods to calculate shock shape in front of a sphere [36], and his work was extended by Hall et al [37]. Using the ideal dissociating gas model (diatomic gas), Hornung investigated nonequilibrium flow over spheres and cylinders [38].…”

Section: A Criteria For Selection Of Experimental Test Conditionsmentioning

confidence: 99%

Experimental and Numerical Investigation of Hypervelocity Carbon Dioxide Flow over Blunt Bodies

Sharma¹,

Swantek²,

Flaherty³

et al. 2010

Journal of Thermophysics and Heat Transfer

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This paper represents ongoing efforts to study high-enthalpy carbon dioxide flows in anticipation of the upcoming Mars Science Laboratory and future missions. The work is motivated by observed anomalies between experimental and numerical studies in hypervelocity impulse facilities. In this study, experiments are conducted in the hypervelocity expansion tube that, by virtue of its flow acceleration process, exhibits minimal freestream dissociation in comparison with reflected shock tunnels, simplifying comparison with simulations. Shock shapes of the laboratory aeroshell at angles of attack of 0, 11, and 16 deg and spherical geometries are in very good agreement with simulations incorporating detailed thermochemical modeling. Laboratory shock shapes at a 0 deg of attack are also in good agreement with data from the LENS X expansion tunnel facility, confirming results are facility-independent for the same type of flow acceleration. The shock standoff distance is sensitive to the thermochemical state and is used as an experimental measurable for comparison with simulations and two different theoretical models. For low-density small-scale experiments, it is seen that models based upon assumptions of large binary scaling values do not match the experimental and numerical results. In an effort to address surface chemistry issues arising in high-enthalpy groundtest experiments, spherical stagnation point and aeroshell heat transfer distributions are also compared with the simulation. Heat transfer distributions over the aeroshell at the three angles of attack are in reasonable agreement with simulations, and the data fall within the noncatalytic and supercatalytic solutions.

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“…For non-equilibrium flows, Lick applied inverse methods for the flow over a sphere 32 and his work was extended by Hall et al 33 Using the ideal dissociating gas model, Hornung investigated non-equilibrium flow over spheres and cylinders. 34 Extending Hornung's original work, Wen and Hornung carried out a joint theoretical and experimental study of non-equilibrium dissociating flow over spheres and developed a model for the stand-off distance in terms of a reaction rate parameter.…”

Section: A Criteria For Selection Of Experimental Test Conditionsmentioning

confidence: 99%

Expansion Tube Investigation of Shock Stand-Off Distances in High-Enthalpy CO2 Flow Over Blunt Bodies

Sharma

Swantek

Flaherty

et al. 2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The shock standoff distance in front of a blunt body is sensitive to the thermochemical state of the free stream. Recently, experimental and numerical studies have reported significantly different bow shock profiles in high-enthalpy carbon dioxide flows, a discrepancy that may result from non-equilibrium processes during flow acceleration in ground-based facilities. In this work, an expansion tube is used to create a Mach 5.7 carbon dioxide flow, matching the stagnation enthalpy and the velocity of previous studies. Images of shock layers are obtained for spherical geometries and a scaled model of the Mars Science Lander. Different sphere diameters are used in order to access non-equilibrium and equilibrium stagnation line shock profiles predicted by theory. Mars Science Lander profiles at zero angle of attack are in good agreement with available data from the LENS X expansion tunnel facility, confirming results are facility-independent for the same type of flow acceleration, and indicating the flow velocity is a suitable first-order matching parameter for comparative testing. Heat transfer measurements on the Mars Science Lander are also presented for the three different angle of attacks, and the results are consistent with previous studies. Initial results from a proposed organo-metallic based emission spectroscopy technique for bow shock layer interrogation are also presented.

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Blunt-Nose Inviscid Airflows With Coupled Nonequilibrium Processes

Cited by 9 publications

References 4 publications

Hypersonic and High-Temperature Gas Dynamics, Second Edition

Hypersonic and High-Temperature Gas Dynamics, Second Edition

Experimental and Numerical Investigation of Hypervelocity Carbon Dioxide Flow over Blunt Bodies

Expansion Tube Investigation of Shock Stand-Off Distances in High-Enthalpy CO2 Flow Over Blunt Bodies

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