PRESSURE DISTRIBUTION ON A CONE-CYLINDER-FLARE BODY AT MACH 14 IN THE PRESENCE OF FLOW SEPARATION.
AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO
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Surface pressure data are presented for a cone-cylinder-flare body with 20 deg and 40 deg flare angles at a nominal freestream Mach number of fourteen. Separation of the flow due to the adverse pressure gradient induced by the flare was found in both cases. Appreciable extent of separation existed in the 40 deg flare case, while for the 20 deg flare separation was less severe. A correlation formula using the viscous interaction parameter is shown to be valid for a wide range of Mach numbers and model geometries. Author
- Research and Experimental Aircraft
- Unmanned Spacecraft