Improvements to an Euler aerodynamic method for transonic flow analysis

Abstract

Modifications to a three-dimensional Euler aerodynamic method (TEAM) and their effect on the accuracy of transonic flow simulations are described. TEAM'S solution algorithm is based on a finite-volume spatial discretization and multistage time-stepping algorithm to solve the Euler equations. Treatment of numerical dissipation and surface boundary condition are specifically addressed. The modified code includes the standard adaptive dissipation scheme using blended second and fourth differences and a flux-limited dissipation scheme. Improved treatment of the surface boundary condition minimizes spurious entropy production. TEAM computations are correlated with experimental data for two wings, ONERA M-6 and Wing C, and an arrow wing-body configuration. For Wing C, the TEAM predictions are also compared with those of the full-potential TWING code on identical grids.

Off-design performance of hypersonic waveriders

“…This computer program is based on the FLO-57 algorithm developed by Jameson et al 26 Lockheed has made major refinements to the method over the past several years. 27 ' 29 In the TEAM code, the region surrounding a given configuration is subdivided into small cells. In each of the cells, the time-dependent Euler (or Navier-Stokes) equations (in integral equation form), representing mass, momentum, and energy conservation, are integrated in time using a multistage Runge-Kutta scheme.…”