NASA NTRS · 19720005622
Computer program for calculating supersonic flow on the windward side conical delta wings by the method of lines
Abstract
A user's manual is presented for a program that calculates the supersonic flow on the windward side of conical delta wings with shock attached at the sharp leading edge by the method of lines. The program also has a limited capability for computing the flow about circular and elliptic cones at incidence. It provides information including the shock shape, flow field, isentropic surface-flow properties, and force coefficients. A description of the program operation, a sample computation, and a FORTRAN 4 program listing are included.
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Klunker, E. B., South, J. C., Jr., Davis, R. M.. 1972-01-01. Computer program for calculating supersonic flow on the windward side conical delta wings by the method of lines. https://ntrs.nasa.gov/citations/19720005622
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