Tables of derivatives to extend the zero incidence cone tables to intermediate mach numbers and cone angles

Report (1966)
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Published Date

31-05-1966

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National Research Council Aeronautical Report LR 451

Abstract

Derivatives witb respect ta cone semi-angle and free-stream Mach number are presented for fight of tbe flow field quantities tabulated in Reference 1 for the case of supersonic flow of an ideal gas (y = 1. 400) about circular cones at zero incidence. Tbe derivatives may be used in a first-order expansion ta comp.tte the essential properties of tbis flow at the shock wave and at tbe surface of cones of any semi -angle and at any free-stream Mach number within tbe range treated in Reference 1. An account is given of the methods used ta obtain these derivatives

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