Abstract
The objective of this study is to evaluate the aerodynamic effects of leading-edge slats on rotor blades under high-speed forward- ight conditions. A partial-span leading-edge slat is proposed for the inboard portion of the existing UH-60A rotor. Some two-dimensional slat studies are done to optimize the slat orientation at low subsonic Mach numbers. A multizone unsteady three-dimensional compressible Navier Stokes solver is developed to compute such rotor/slat con gurations. The rotor wake is captured from rst principles. Some forward- ight results are presented for the UH-60A slatted rotor and compared with the baseline rotor case. The surface pressures and the force coef cients indicate that the slat is bene cial in reducing the retreating side dynamic stall. It was found that the slat reduces the torque and pitching moments on the retreating side compared to the baseline con guration.
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