Numerical Computation of Flows about an Aircraft with Flow-through Inlet

An Euler solver which can use arbitrary multi-block grid systems has been developed. This solver uses MUSCL approach for the higher order of spatial discretization error. Furthermore, it has the exit boundary condition given in terms of mass flow rate so that it can simulate the flows through engine inlet. The flow-through exit boundary condition, unlike Murman's method, does not have to regenerate inlet duct grid for the different mass flow rates. The solver has been tested on a generic missile and its results have been compared with the experimental and computational results. Mixed internal and external flows around a jet trainer with a pitot type inlet have been computed.