Supersonic nozzle contour design using the method of characteristics with boundary layer corrections

This paper describes the method used to design a two dimensional convergent/divergent nozzle using the method of characteristics. The principle of conservation of mass was used in the subsonic region and "Pucketts" Method of Characteristics, in the supersonic region. The inviscid contour was then corrected by the displacement thickness of the boundary layer. A laminar or turbulent boundary layer was calculated using the compressible von Karman Momentum Integral. A sample problem is attached with several recommendations for improvement. A listing of the computer code is also included in the report.