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 thick limits and numerical results are obtained for the effects of radiation on the structure of the shock wave, and the structure of the boundary layer, including some effects on heat transfer rate to the vehicle.Contents.
List of figures.
Abstract.
Introduction.
Symbols.
Governing equations for radiating flows.
Radiation in a shock wave.
Radiation in a boundary layer.
Discussion of results.
Conclusions.
Acknowledgments.
References.
Table - gas properties.
Appendix.
Figures.
