Multiple‐Zone Potential Solution around Wing‐Body Configurations

An existing computer code to solve a supersonic potential equation around three‐dimensional configurations was modified. Using a generalized boundary‐conforming coordinate system, a full potential equation in conservation form was upwind differenced in supersonic direction. Grids were generated in each two‐dimensional cross‐flow plane using the algebraic method. A new topology for grid generation produced appropriate grids around thin wings and wing bodies. Usage of orthogonal grid generation in cross‐flow plane improved results and extended the various cases that can be handled by the code. A zonal flow field solution was obtained using a new method for the implementation of boundary conditions at wing locations on boundaries of each zone. Approximate factorizations were used to solve the resulting equations implicitly. Using these capabilities thin‐wing and wing‐body results are presented that compare well with other results. The capability of running this code on microcomputers makes this program a potentially valuable design tool in primary and middesign stages.