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Heat Transfer in Hypersonic Flow with Radiation and Chemical Reaction by Scala S.M., Sampson D.H. is a nonfiction available to read on EtoBox.

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AGARD—21, R63SD46, London, England, 1963. — 80 pp. — (Presented at the Twenty-First AGARD Combustion and Propulsion Meeting on Supersonic Flow, Chemical Processes and Radiative Transfer. Space sciences laboratory, Aerophysics section. London, England, April 1-5, 1963). During hypervelocity flight, the heat transfer rate to a space vehicle depends on the contributions of aerodynamic (convective, conductive, diffusive and chemically reactive) transport phenomena and radiative transport processes. For certain combinations of vehicle flight speed, altitude, vehicle geometry and planetary gas composition, it is possible for the radiative transport to be of comparable magnitude to, or even to predominate over, the aerodynamic processes, and hence, the twin problems of aerodynamic and radiative heat transfer should be treated self-consistently. The macroscopic equations for the conservation of mass, momentum and energy (including radiative contributions) are first presented. The hypervelocity flow field is then considered to consist of three definable regions; namely, the shock wave, the influscid flow and boundary layer. The equations are treated for the optically thin and optically thic

Who reads Heat Transfer in Hypersonic Flow with Radiation and Chemical Reaction?

Author

Scala S.M., Sampson D.H.

Language

EN

Category

nonfiction

Subjects

Science, Physics, Stem