鸭翼-前掠翼气动布局纵向气动特性实验研究

前掠翼布局由于其潜在的优势,在未来战斗机的研制中将占有日益重要的地位.本实验通过可变前掠翼和鸭式前翼布局的风洞测力实验,重点分析比较了平板机翼在不同掠角下的纵向气动性能以及鸭翼的影响.实验结果表明,前掠翼在大迎角时能有效提高模型的升力系数,小迎角时其升阻比也略优于后掠翼.前掠翼布局能有效推迟失速,具有良好的失速特性;前掠角较大时,升力系数曲线在失速迎角附近有一个升力系数的"平台",该布局具有"缓失速"特性.距离主机翼较远的鸭式前翼(模型M2)在主机翼前掠和后掠情况下,均可改善整体布局的失速特性,增大失速迎角,增强前掠翼布局缓失速的特点.近距耦合鸭翼(模型M3)显著提高了模型在大迎角下的升力系数.另外,主翼前掠和鸭式前翼布局飞行器具有较好的机动性.

Experimental investigation on longitudinal aerodynamic characteristics of Canard-Forward-Swept wing configuration

FSW (Forward-Swept-Wing) configuration is one of preponderant conceptions in the design of future generation fighter aircraft. The authors investigate experimentally the effect of canard wing and sweep angle on longitudinal aerodynamic characteristics of canard-forward-swept wing configuration by means of forces measurement in wind tunnel. The results indicate that the lift characteristics of FSW outweigh that of backswept wing at high angle of attack; FSW has higherstalling angle and keeps higher lift coefficient in a broader range of angle of attack near stalling angle, which is improved by canard wing located farther away from the main wing. A coupled canard wing can increase the lift coefficient of overall configuration. Meanwhile Canard-forward-swept wing has an excellent maneuverability.