![]() Glaz B, Goel T, Liu L, Friedmann PP, Haftka RT (2009) Multiple-surrogate approach to helicopter rotor blade vibration reduction. Sun H, Lee S (2005) Response surface approach to aerodynamic optimization design of helicopter rotor blade. Le Pape A, Beaumier P (2005) Numerical optimization of helicopter rotor aerodynamic performance in hover. NREL/SR-500-26173, National Renewable Energy Lab., Golden, CO (US) ![]() Giguere P, Selig MS (1999) Design of a tapered and twisted blade for the NREL combined experiment rotor. Walsh JL, Bingham GJ, Riley MF (1987) Optimization method applied to the aerodynamic design of helicopter rotor blades. ![]() The results also confirm that the optimum swept-tapered blade with cambered airfoil lowers the power required in hover by about 7% and enhances the FM up to 10% with an acceptable improvement relative to the rectangular planform with NACA 0012 cross section.Īirfoil class function \( \barr \) ψ The results show that this procedure alleviates the challenges associated with complex and time-consuming approaches required computational fluid dynamics CFD analysis. The SCD data were generated through the in-house flight dynamic simulation program in which the model of rotor is a nonlinear dynamic model developed for rotors and the unsteady aerodynamic representation with a three-state dynamic inflow model. Therefore, the systematic evaluation of blade taper, taper point on the blade, linear twist, tip sweep, and airfoil shape coefficients on figure of merit (FM), rotor thrust, and power required is provided with the proposed procedure. ![]() The procedure emphasizes small composite data (SCD), airfoil representation method, and numerical optimization and is presented as generalized process to the rotor blade design optimization problem. In this paper, blade planform effects and airfoil shape coefficients on aerodynamic efficiency of helicopters in hover flight are investigated. ![]()
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