An exact solution for linearized problem of supersonic airflow over a flat relief
Propulsion and Power Plants
Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia
Theoretical results for shock-wave drag value estimation taking into consideration a surface relief exist only for some simple relief forms. Nearly all of them are obtained by solving of a boundary problem for a linear second-order partial differential equation derived by Blokhintsev. This boundary problem is solved in the paper analytically for a case of two-dimensional supersonic flow near reliefed surface. An arbitrary form of the relief is suggested.
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