Abstract
In this study, a new three-dimensional fully iterative parabolized Navier-Stokes (PNS) scheme has been developed to study perfect-gas or equilibrium-air viscous hypersonic flows around ballistic re-entry configurations at large angles of attack. This three-dimensional PNS scheme is inherently stable in the subsonic as well as the supersonic flow regions and, thus, does not require any sublayer approximation. Furthermore, it uses a generalized PNS formulation to treat perfect-gas and equilibrium-air gas models in a unified manner. A second-order smoothing approach is used to damp the solution oscillations, whereas a pseudo-unstead y approach is used to significantly enhance computational efficiency without compromising solution accuracy. A new fully implicit and crossflowcoupled shock-fitting approach has been used, along with a new predictor-corrector solution scheme to treat large crossflow-separated regions. The flow over a 15-deg sphere-cone configuration at an angle of attack of 20 deg is studied at two different Mach numbers to demonstrate the solution scheme.
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