Development and application of Spalart–Allmaras one equation turbulence model to three-dimensional supersonic complex configurations

This paper presents an extension of Spalart–Allmaras model to compressible supersonic flows. The model is implemented in a three-dimensionnal structured multi domain code using a high resolution implicit upwind scheme. Details of the formulation as well as the treatment of viscous gradients near boundaries are given. The method is validated for two different configurations. Firstly a cruciform missile simulation shows the ability of the method to capture accurately the interaction between the fuselage vortices and the winglets enabling the correct evaluation of the roll induced moment. Secondly an internal inlet flow computation including bleeds and struts demonstrates the usefulness and the accuracy of the method for multiple boundary layers supersonic complex configurations.