This paper contains a tabulation of functions of the Mach number which are frequently used in high-speed aerodynamics. The tables extend from M = 0 to M = 10.0 in increments of 0.01 and are based on the assumption that air is a perfect gas having a specific heat ratio of 1.400.
Compressible Flow Tables for Air
01.01.1947
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Englisch
Compressible flow tables for air
Engineering Index Backfile | 1948
|Compressible flow tables for air
TIBKAT | 1948
|Compressible flow tables for air
NTRS | 1948
|Equations, tables, and charts for compressible flow
Engineering Index Backfile | 1953