The two-dimensional compressible unsteady Navier-Stokes equations are computed with a second-order accurate Non-MUSCL TVD scheme to obtain the steady-state solution according to the time-dependent method. The shock wave is successfully captured with a good resolution at both transonic and supersonic regions, and the capturing process is analysed. The comparison of the higher-order accurate is made in order to demonstrate the difference of the resolution to shock waves. The process of approaching the steady state with the time-dependent method is explained. In addition, the interation of shock waves for different Mach numbers and ifferent angles of attack are described by showing the local flow situation at the interaction region.
|Title of host publication||American Institute of Aeronautics and Astronautics|
|Publisher||American Institute of Aeronautics and Astronautics Inc. (AIAA)|
|Publication status||Published - 22 Aug 2012|
|Event||9th International Space Planes and Hypersonic Systems and Technologies Conference - Norfolk, United States|
Duration: 1 Nov 1999 → 5 Nov 1999
|Conference||9th International Space Planes and Hypersonic Systems and Technologies Conference|
|Period||1/11/99 → 5/11/99|