Accession Number : AD0267907

Title :   Shock Curvature due to Boundary Layer Effects in Shock Tube,

Corporate Author : AEROSPACE CORP EL SEGUNDO CALIF

Personal Author(s) : HARTUNIAN,R.A.

Report Date : 20 DEC 1960

Pagination or Media Count : 1

Abstract : The analysis and result of a two-dimensional, linearized treatment, including real gas effects, are presented. An expression for shock shape as a function of shock Mach number and initial pressure of the test gas is presented. Results are compared with available experimental data obtained in argon at low shock strengths and inAIR AT HIGH SHOCK Mach numbers. Within the scatter of the data in the latter experiments, there is relatively good agreement with theory, while theory falls approximately 30 + or - 10% above the data in argon. Some disagreement is attributed to application of the two-dimensional theoretical result to axisymmetric shock tubes of finite dimensions used in the experiments. (Author)

Descriptors :   *BOUNDARY LAYER, *SHOCK WAVES, ARGON, DIFFERENTIAL EQUATIONS, EXPERIMENTAL DATA, GAS FLOW, HEAT TRANSFER, HIGH TEMPERATURE, INTEGRAL TRANSFORMS, KINETIC THEORY, PERTURBATION THEORY, PRESSURE, SHOCK TUBES

Distribution Statement : APPROVED FOR PUBLIC RELEASE