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

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

Ohman, L.H.

National Research Council Canada, National Aeronautical Establishment, High Speed Aerodynamics

1964-12-31

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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National Research Council Canada

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National Research Council Aeronautical Report LR 419

Aerospace Engineering Reports

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(c)1964 National Research Council Canada