Accession Number : AD0438261


Title :   THE INVISCID FLOW OF REACTING AND RADIANT AIR PAST A HYPERSONIC BLUNT BODY,


Corporate Author : BOEING CO SEATTLE WASH


Personal Author(s) : Kennet,Haim


Report Date : 15 OCT 1960


Pagination or Media Count : 40


Abstract : The inviscid hypersonic flow around an arbitrary blunt body of revolution has been formulated for machine computation. The highly accurate streamtube continuity method was extended to cover the case of chemically reacting and thermally radiating optically thin air, when the flow is in complete thermodynamic and chemical equilibrium. An extension to the case of opaque air is also given for the special case of a spherical nose of unit surface emissivity. The present schem calculates the flow field well into the pure supersonic region at which point currently existing techniques, such as the method of characteristics, can be applied. (Author)


Descriptors :   (*BLUNT BODIES, HYPERSONIC CHARACTERISTICS), VISCOSITY, THERMODYNAMICS, ABSORPTION, GEOMETRY, SHOCK WAVES, AIR, VELOCITY, THERMAL RADIATION, ATMOSPHERE ENTRY, REFLECTION, EMISSIVITY, SUPERSONIC CHARACTERISTICS, CHEMICAL REACTIONS, CONICAL BODIES


Distribution Statement : APPROVED FOR PUBLIC RELEASE