The prediction capabilities of unstructured primitive-variable and vorticity-transport-based Navier-Stokes solvershave been compared for rotorcraft-fuselage interaction. Their accuracies have been assessed using the NASALangleyROBIN series of experiments. Correlation of steady pressure on the isolated fuselage delineates the differencesbetween the viscous and inviscid solvers. The influence of the individual blade passage, model supports, andviscous effects on the unsteady pressure loading has been studied. Smoke visualization from the ROBIN experimenthas been used to determine the ability of the codes to predict the wake geometry. The two computational methodsare observed to provide similar results within the context of their physical assumptions and simplifications in the testconfiguration.
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