Validation of computational results of Rotor/Fuselage interaction analysis using rFlow3D code
摘要
A newly developed rotor flow solver: rFlow3D is applied to an isolated helicopter fuselage in the freestream, and then to a rotor/fuselage combination to analyze the surrounding flow field and study the effects due to the rotor/fuselage interaction. The modified SLAU scheme, which stands for Simple Low-dissipative AUSM (Advection Upstream Splitting Method), is a type of locally preconditioned numerical scheme. It enables the solver to calculate realistic drag coeffi cient values even at low speeds under Mach 0.01 as well as those at transonic speeds. This favorable feature of the scheme is suitable for the challenging demands for predicting the flow fields surrounding helicopters. The solver is based on overlapped grid approach. The ROBIN type fuselage was adopted as the geometry for both the isolated fuselage and rotor/fuselage simulations. Experimental settings for the controls and other conditions are used in the calculations. The resulting flow field variables were then compared to the experimental measurements. It was concluded that the newly developed code provides satisfactory results. Flow features around the rotor blade root and in other low speed areas are improved and test calculations to date are promising for future applications in the analysis of flow fields surrounding helicopters.