Transonic Drag Reduction with Contour Bump on a Supercritical Airfoil
The effect of contour bumps on transonic drag reducing at off-design conditions of a supercritical airfoil have been examined in the paper. Research focuses on twodimensional flow condition with Mach number of 0.78 and chord Reynolds number of 2.5 million. Different contour bump airfoil configurations are examined using numerical method. Recent tests on these models are conducted in 0.6m×0.6m transonic wind tunnel at CARDC to validate the drag reduction effect. The computational results indicate that a surface contour bump is capable of reducing transonic drag for moderate to high lift conditions, but raises the drag remarkably for lower lift condition due to the second shock wave generated near the aft of the bump. The experimental research shows a good agreement with the computational. With the computational and experimental evidences, the mechanism of contour bump’s effect on transonic drag reduction has been further analyzed.
Contour Bump Drag Reduction Wind Tunnel Test Numerical Simulation
Liu Guangyuan Tao Yang Guo Qiuting Sun Yan
State Key Laboratory of Aerodynamics China Aerodynamic Research and Development CenterP.O.Box 211 Mi State Key Laboratory of Aerodynamics China Aerodynamic Research and Development Center P.O.Box 211 M State Key Laboratory of Aerodynamics China Aerodynamic Research and Development CenterP.O.Box 211 Mianyang, 621000, Sichuan, China
国际会议
三亚
英文
613-616
2012-01-06（万方平台首次上网日期，不代表论文的发表时间）