Relating Vorticity Confinement to the Menter Shear Stress Transport Turbulence Model

摘要

The U.S. Army Aviation and Missile Research, Development, and Engineering Center (AMRDEC) has been applying a Government-developed, productivity-oriented, Computational Fluid Dynamics (CFD) methodology to the aerodynamic design of Army missiles. This methodology, dubbed Euler Tunnel Analysis (ETA), uses automated grid generation software and a robust Euler solver to drastically reduce the time required to set up and execute flowfield computations. In addition, it has the capability to exercise the vorticity confinement technique in the field (to preserve tip vortices) and on the body surface (to mimic viscous effects). ETA was applied to a supersonic missile configuration with a high fineness ratio body, low aspect ratio tail fins, and a deflectable nose (used for aerodynamic control). In addition, an equation was derived to relate the surface confinement coefficient to physical parameters. Computations were made with and without vorticity confinement. Afterwards comparisons were made against wind tunnel data to assess ETA's ability to produce meaningful results. It was found that the equation yielded reasonably successful values for the surface coefficient. It was also observed that the use of surface vorticity confinement improved the accuracy of normal force, pitching moment, and yawing moment calculations.