Solution for 2-dimensional flow of inviscid gas is obtained by numerical methods of analysis, divided into subsonic region analyzed by relaxation method of Southwell and supersonic region treated by method of characteristics; shapes of sonic line and shock wave are obtained by iteration techniques; distribution in flow pattern indicates interaction between subsonic and supersonic regions is negligible; comparisons with theoretical and experimental results.
Numerical solution of flow of perfect gas over circular cylinder at infinite mach number
NASA -- Memo
National Aeronautics and Space Administration -- Memorandums ; Memo n 2-25-59A
1959
33 pages
Report
English
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