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Normal- and oblique-shock flow parameters in equilibrium air including attached-shock solutions for surfaces at angles of attack, sweep, and dihedralNormal- and oblique-shock flow parameters for air in thermochemical equilibrium are tabulated as a function of shock angle for altitudes ranging from 15.24 km to 91.44 km in increments of 7.62 km at selected hypersonic speeds. Post-shock parameters tabulated include flow-deflection angle, velocity, Mach number, compressibility factor, isentropic exponent, viscosity, Reynolds number, entropy difference, and static pressure, temperature, density, and enthalpy ratios across the shock. A procedure is presented for obtaining oblique-shock flow properties in equilibrium air on surfaces at various angles of attack, sweep, and dihedral by use of the two-dimensional tabulations. Plots of the flow parameters against flow-deflection angle are presented at altitudes of 30.48, 60.96, and 91.44 km for various stream velocities.
Document ID
19760004931
Acquisition Source
Legacy CDMS
Document Type
Special Publication (SP)
Authors
Hunt, J. L. (NASA Langley Research Center Hampton, VA, United States)
Souders, S. W. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1975
Subject Category
Aerodynamics
Report/Patent Number
NASA-SP-3093
Accession Number
76N12019
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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