An interactive three-dimensional laminar and turbulent boundary-layer method for compressible flow over swept wings
A three-dimensional laminar and turbulent boundary-layer method is developed for compressible flow over swept wings. The governing equations and curvature terms are derived in detail for a nonorthogonal, curvilinear coordinate system. Reynolds shear-stress terms are modeled by the Cebeci-Smith eddy-viscosity formulation. The governing equations are descritized using the second-order accurate, predictor-corrector finite-difference technique of Matsuno, which has the advantage that the crossflow difference formulas are formed independent of the sign of the crossflow velocity component. The method is coupled with a full potential wing/body inviscid code (FLO-30), and the inviscid interaction is performed by updating the original wing surface with the viscous displacement surface calculated by the boundary-layer code. The number of these global iterations ranged from between seven to twenty depending on the Mach number, sweep angle, and angle of attack. Several tests cases are computed by this method and the results are compared with another inviscid-viscid interaction method and with experimental values.
- Research Organization:
- North Carolina State Univ., Raleigh, NC (USA)
- OSTI ID:
- 5172255
- Country of Publication:
- United States
- Language:
- English
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