SPACE-MARCHING CALCULATIONS ABOUT HYPERSONIC CONFIGURATIONS USING A SOLUTION-ADAPTIVE MESH ALGORITHM

A solution-adaptive marching algorithm is developed and applied to a t hree-dimensional parabolized Navier-Stokes equation solver. The result ing algorithm obtains accurate solutions by using a spatial-marching/a daptive-grid procedure. The adaptation step redistributes grid points line by line in both crossflow directions, with grid point motion cont rolled by forces analogous to tensional and torsional spring forces wi th the tensional force proportional to the error measure or weighting functions. The solution-adaptive marching procedure is applied to the hypersonic flow about two generic aircraft configurations. The first o f these is an all-body-type geometry with elliptical cross sections an d is studied at angles of attack of 0, 5, and 15 deg. The second geome try is a generic blended-wing-body design. Results are presented that demonstrate the improvements in flowfield resolution obtainable with t he solution-adaptive marching procedure over conventional fixed grid t echniques. Computed pitot pressure profiles obtained using the solutio n-adaptive algorithm show improved agreement with experimental data co mpared to predictions obtained using a fixed grid.