The thin-layer, three-dimensional compressible Navier-Stokes equations are solved for hypersonic afterbody flowfields over capsule-type re-entry vehicles at high angles of attack. In the report, an implicit approximate factorization method has been used to obtain numerical solutions under the following free stream condition: free stream Mach number of 7.0 with Reynolds number of 4.5 x 100,000, which is the same condition as in the hypersonic wind tunnel at the National Aerospace Laboratory. Body configurations are composed of a blunt-nosed forebody and 20 deg conical afterbody followed by a cylinder. The results demonstrate the capability of the present numerical procedure for investigating the detailed structure of such three-dimensional separations and the effects of afterbody to the total aerodynamic performance.
Navier-Stokes Solution of Three-Dimensional Hypersonic Afterbody Flowfields over Capsule-Type Vehicles
1984
32 pages
Report
No indication
English
A study of hypersonic afterbody flowfields
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