Abstract
Transonic turbulent flows inside two-dimensional and conical nozzles have been analyzed by solving twodimensional Navier-Stokes equations. The governing equations are written in a conservative form of a general curvilinear coordinate system and are solved by a hopscotch numerical method. An algebraic two-layer turbulence model is used in the computation. Good agreement is obtained between the solutions and experimental measurements for all of the cases investigated, including both the forward-thrust and thrust-vectoring cases. Among these, a two-dimensiona l nozzle in a stalled condition; that is, a reverse flow occurring at the nozzle exit, as well as the case of a supersonic exhaust nozzle with an external flow turning, are of particular interest because of the strong viscous and inviscid flow interaction. Good agreement is achieved between computed and measured pressure distributions. The viscous effects on shock location and shock strength are accurately predicted.
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