Numerical Simulation for the Flow around a Tactical Missile at High Angles of Attack Using the Navier-Stokes Equations

摘要

High incidence flow around a tactical missile is numerically simualted at supersonic speed using the MUSCL FVS scheme. The flow near the wings is simulated with the composite-block grid technique in detail. Some useful conclusions are drew through analysis the flow filed, which generally includes the separated flow at the leeward side of the fuselage and the wings.