Validation of the Flow Solver CODA for Viscous and Inviscid Supersonic Flows

Abstract

The DLR Tau Code is widely used in German academia and industry to solve the Reynolds - Averaged Navier-Stokes equations for external aerodynamic flows from subsonic to hypersonic Mach numbers. However, its development began in the 1990s and it is not ensured that computations using Tau scale well on current High Performance Computers , which use either thousands of cores or a mixed CPU / GPU architecture. Therefore, the flow solver CODA (CFD for ONERA, DLR, and Airbus) based on current object oriented programming paradigms is developed to replace the DLR Tau Code. To verify CODA for supersonic flows, which occur at expendable or reusable space vehicles, a 2D cylinder in a Ma = 1.7 crossflow is computed using the DLR Tau Code and CODA and compared with literature data. A good match within 3 % of drag and surface pressure data is observed. Furthermore, a 3D clean cylinder in a Ma = 2.98 flow at an angle of attack of 5° at its blunt face is computed and drag and heat flux data produced with the DLR Tau Code and CODA will be compared in the final paper.