基于转捩的雷诺数对翼型气动特性影响计算与实验研究OA

A flow transition prediction method for calculating effects of Reynolds numbers on aerodynamic characteristics of airfoil is developed,and the accuracy of the method is verified by wind tunnel experiment data and other calculation results.On these basics,the infrared thermal imager experiment results of the flow transition in low-speed wind tunnel and the aerodynamic characteristics experiment results with variable Reynolds number in high-speed wind tunnel are carried out respectively,and compared with the numerical results of helicopter rotor airfoil.Specially,effects of Reynolds numbers on airfoil aerodynamic characteristics by means of flow transition under different working conditions are researched and some meaningful conclusions are obtained.The calculation method,experiment method and results as well as the flow transition analysis conclusions for aerodynamic characteristics can be used for the design of helicopter rotor airfoil,especially for the helicopters under the high altitude and low Reynolds number working conditions.