Numerical Solutions of Supersonic and Hypersonic Laminar Compression Corner Flows
Numerical Solutions of Supersonic and Hypersonic Laminar Compression Corner Flows
An efficient time-splitting, second-order accurate, numerical scheme is used to solve the complete Navier-Stokes equations for supersonic and hypersonic laminar flow over a two-dimensional compression corner. A fine, exponentially stretched mesh spacing is used in the region near the wall for resolving the viscous layer. Good agreement is obtained between …