A surface flow solution and stability derivates for bodies of revolution in complex supersonic flow. Part II. Results for two families of bodies of revolution for. 1.1 ≤M≤5

Report (1964)

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31-12-1964

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National Research Council Aeronautical Report LR 419

Abstract

Stability data are presented for two families of bodies ; cone -cylinder and ogive-cylinder configurations with nose fineness ratios of 7 , 5 and 3 and lengths of the cylindrical section up to 15 diameters, for Mach numbers 1.1 to 5. The tabulated results include, apart from the stability derivatives, disturbance velocities and pressure coefficient derivatives. Boundary layer displacement effects are included for the cone-cylinder cases with a nose fineness ratio of 5.

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