抄録
The present paper describes the numerical and experimental results on unsteady nozzle flows induced by nonstationary shock waves. The two-dimensional Navier-Stokes equations are numerically solved using the upwind TVD finite-difference scheme of the Harten-Yee type. For the purpose of computational visualization of shock waves in transient nozzle starting process, computer shadowgraphs are developed based on the principle of the optical shadowgraph. Visualization experiments employing a conventional shock tube are also performed. Comparison of numerical and experimental results shows satisfactory agreement. Furthermore, the steady flow establishment process around an airfoil model installed inside the nozzle is numerically investigated. The simulated results successfully reveal the unsteady viscous flow structure around the model.
