Accession Number : AD0641249

Title :   NONEQUILIBRIUM SHOCK EXPANSION METHOD AS A SIMPLE WAVE PERTURBATION.

Descriptive Note : Final technical rept.,

Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE AEROPHYSICS LAB

Personal Author(s) : Shih,W. C. L.

Report Date : JUL 1966

Pagination or Media Count : 68

Abstract : Shock expansion theory is useful for evaluating pressure distributions, flow field properties and shock shapes on airfoils and bodies with attached shock waves in supersonic perfect gas flows. This method is much simpler than the method of characteristics and yet gives accurate results which cannot be duplicated by purely linear theories. The nonequilibrium flow of a vibrating diatomic gas is treated as a perturbation of the perfect gas shock expansion flow field. The perturbation parameter is taken to be the ratio of a reference vibrational energy to (gamma-1) times the total enthalpy. Solutions in terms of quadratures are obtained for the effects of vibrational nonequilibrium on wedge flow, Prandtl-Meyer flow and the flow about a curved airfoil. The integrals in the wedge flow case may be carried out analytically and the existence of an entropy layer on the body and a relaxation layer near the shock is deduced. (Author)

Descriptors :   (*SUPERSONIC FLOW, NONEQUILIBRIUM FLOW), SHOCK WAVES, THEORY, PERTURBATION THEORY, VIBRATION, DIATOMIC MOLECULES, WEDGES, AIRFOILS, THERMODYNAMICS

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE