超临界翼型跨音速特性实验研究

针对新设计的超临界翼型，采用风洞实验方法验证和评估了其气动特性。在增压连续式跨音速风洞(NF-6风洞)开展了超临界翼型跨音速特性的实验研究，验证了该翼型设计的压力分布曲线特点。激波位置和波后压力平台区长度表明设计结果和实验结果基本一致，揭示了超临界翼型跨音速的气动特性;阻力发散马赫数达到期望的设计指标，探讨了雷诺数对该翼型气动特性的影响。最后采用升华法实现了翼型表面流动特性的显示。结果表明转捩点约在16%弦长位置。

Experimental Investigation of the Supercritical Airfoil Transonic Characteristics

Aiming the newly designed supercritical airfoil, its aerodynamic performance was validated and evaluated by wind tunnel experiment. Experimental investigation on supercritical airfoil transonic characteristics was firstly carried out based on pressurized continuous transonic wind tunnel (NF-6 wind tunnel), which verifies the pressure distribution characteristics of this airfoil. Experimental results show that the shock wave position and the pressure platform length after shock wave are consistent with designed target, which reveals its aerodynamic performance. The drag-divergence Mach number achieves desired specifications. The effect of Reynolds number on its aerodynamic performance was discussed. Finally, the flow pattern over airfoil was demonstrated by sublimation method. It shows that the turning point appears at the position about 16% chord length.