Validation and Modification on the "Super3" Code.

Abstract

A code for the computation of unsteady supersonic flows around oscillatory wings and complete aircraft configurations is described. The code sovles the linearised steady and unsteady supersonic potential equations by a Finite Difference method. The original code was significantly improved with respect to the treatment of subsonic leading edges. Solutions for such cases are now nearly free of numerical oscillations. Furthermore, the code is supplied with user- friendly input (geometry, unsteady modes) and output routines as wellas with graphic pre- and postprocessing tools. The new code is validated by comparison with other numerical results from both an analytical and a potential gradient method for simple wings and with results from a non-liner Euler code for a realistic supersonic transport wing design. The agreement of the results is very satisfying. The new code is fast and allows unsteady supersonic computations for a whole aircraft configuration within a few seconds on a workstation. It is very well suited for use on a workstation andmay be used to include aeroelasticity in the design stage of supersonic aircraft.