Stagnation Point Heat Transfer from a Viscous Nongray Radiating Shock Layer PDF Download
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Author: John David Anderson (Jr.)
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 84
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Book Description
Results are presented for several numerical experiments using an analysis of the viscous radiating stagnation region shock layer and stagnation point heat transfer. A simple step model absorption coefficient, rationally constructed from existing quantum mechanical calculations, is shown to accurately predict shock layer nongray continuum radiative heat transfer in comparison to results obtained with detailed spectral absorption coefficients. Sensitivity of the heat transfer to uncertainties in gas radiative and transport properties is also examined, as well as the effect of artificially increased absorption in the boundary layer. (Author).
Author: John David Anderson (Jr.)
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 84
Get Book Here
Book Description
Results are presented for several numerical experiments using an analysis of the viscous radiating stagnation region shock layer and stagnation point heat transfer. A simple step model absorption coefficient, rationally constructed from existing quantum mechanical calculations, is shown to accurately predict shock layer nongray continuum radiative heat transfer in comparison to results obtained with detailed spectral absorption coefficients. Sensitivity of the heat transfer to uncertainties in gas radiative and transport properties is also examined, as well as the effect of artificially increased absorption in the boundary layer. (Author).
Author: John David Anderson (Jr.)
Publisher:
ISBN:
Category : Radiative transfer
Languages : en
Pages : 66
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Book Description
A closed-form equation is derived for stagnation point reentry radiative heat transfer accounting for the combined effects of radiative cooling and nongray self-absorption within the shock layer. The equation can be applied for both continuum and atomic line radiation. In addition, the equation is shown to agree favorably with existing numerical data for stagnation point, continuum radiative heat transfer for a wide variety of conditions. Also, the equation is shown to apply to the end-wall radiative heat transfer behind a strong reflected shock wave in a shock tube. Finally, the equation provides a rapid means of obtaining, by hand, reasonably accurate engineering estimates for reentry radiative heat transfer including shock layer radiative cooling and nongray self-absorption.
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 818
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Book Description
Author: Walter B. Olstad
Publisher:
ISBN:
Category : Blunt bodies
Languages : en
Pages : 92
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Book Description
A singular perturbation solution to the blunt-body stagnation-region flow of an inviscid, radiating gas has been obtained by means of the Poincař-Lighthill-Kuo, or perturbation-of-coordinates, method. A number of results for a gray gas have been presented in order to provide some physical insight into the effects of various parameters on the shock-layer enthalpy profiles and the radiant heat-transfer rates. A nongray absorption-coefficient model was developed which includes, in an approximate way, the important vacuum-ultraviolet contributions of bound-free and line transitions. This model was used to obtain solutions pertinent to the case of reentry into the earth's atmosphere. While the results are restricted to small values of the radiation cooling parameter, which characterizes the relative importance of radiation and convection as energy-transport mechanisms, they cover broad ranges of vehicle velocity, altitude, and nose radius, which are of practical interest. The characteristic enthalpy variation of the model absorption coefficient was found to be nearly independent of altitude and nose radius for fixed vehicle velocity except for velocities lower than 10.67 km/sec. Thus it was possible to correlate certain quantities by plotting these quantities as functions of the nondimensional adiabatic radiant heat-transfer rate for various altitudes and nose radii at fixed vehicle velocity. Among the quantities correlated was the cooling factor (the ratio of the stagnation-point radiant heat-transfer rate to the adiabatic radiant heat-transfer rate). The cooling-factor correlation is particularly useful because it eliminates the need to perform nonadiabatic calculations whenever radiant heat-transfer rates are desired. Also correlated was the factor by which the convective heat-transfer rate is reduced because of radiation losses in the shock layer. Finally, upper-bound estimates were made of the effects of absorption of precursor radiation by the free-stream air on the radiant and convective heat-transfer rates.
Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 962
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Book Description
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 966
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Book Description
Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 956
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Book Description
Author: Walter B. Olstad
Publisher:
ISBN:
Category : Blunt bodies
Languages : en
Pages : 188
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Book Description
Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 432
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Book Description
Author: V.Z. Parton
Publisher: Routledge
ISBN: 1351412930
Category : Technology & Engineering
Languages : en
Pages : 209
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Book Description
Recent government and commercial efforts to develop orbital and suborbital passenger and transport aircraft have resulted in a burgeoning of new research. The articles in this book, translated from Russian, were contributed by the world's leading authorities on supersonic and hypersonic flows and heat transfer. This superb book addresses the physics and engineering aspects of ultra high-speed aerodynamic problems. Thorough coverage is given to an array of specific problem-solving equations. Super- and Hypersonic Aerodynamics and Heat Transfer will be essential reading for all aeronautical engineers, mechanical engineers, mathematicians, and physicists involved in this exciting field of research.
