Inlet flowfields for airbreathing missiles are calculated by a two-dimensional computational method. A supersonic freestream is assumed to allow the forebody calculation to be uncoupled from the inlet calculation. The inlet calculation employs an implicit, time-marching, finite difference procedure to solve the Euler equations formulated in body-fitted coordinates. The method can be used for a flowfield with both subsonic and supersonic regions and is found to converge rapidly for supercritical inlet operation. For subcritical inlet operation, however, convergence to steady state is slow.
Numerical simulation of two-dimensional inlet flowfields
Journal of Aircraft ; 21
1984-04-01
Miscellaneous
No indication
English
Numerical simulation of two-dimensional inlet flowfields
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