Validation of the FLOWer-Code for Aerodynamics of Capsules

Abstract

Numerical flow simulations around a biconic capsule under inviscid supersonic and hypersonic flow conditions are presented and discussed. The numerical solutions are performed with the DLR FLOWer-code for a range of angles of attack upto 60*. The accuracy of the solutions are addressed through out grid convergence studies and comparing results with solutions obtained with the CEVCATS-code, as well as with available experimental data. The results indicate a qualitative and quantitative good agreement between the numerical solutions performed with both computer codes. Also, the comparison of computed aerodynamic coefficients with experimental data shows a very good correlation. However, the tested version of the FLOWer- code is not suitable for engineering applications in supersonic and hypersonic flow problems. Since it is based on a central differencing scheme its rates of convergence are very poor when comparing with the upwind scheme of the CEVCATS-code. The present.