论文部分内容阅读
飞机加装翼尖小翼后可降低翼尖涡的强度,在减少飞机诱导阻力、提高飞行经济性的同时也会降低飞机的尾涡强度,有利于缩减尾涡安全间隔。通过对加装翼尖小翼后飞机低速极曲线的拟合研究,分析了诱导阻力的变化情况,进而提出用当量展弦比来反映翼尖小翼对尾涡涡强度的影响。然后以B737-800和B737-800W飞机的气动原始数据为例,进行了计算分析。结果表明,加装翼尖小翼后的飞机在起降阶段的阻力系数减小量在3%左右,等价于飞机的展弦比提高了4.96%,从而可以降低4.73%的尾涡初始强度,使得相同气象条件下对后机的诱导力矩系数降低约6%~8%,尾涡安全间隔则可以减小3.5%左右。
After the aircraft is equipped with wingtips, the strength of the wingtip vortex can be reduced. While reducing the induced resistance of the aircraft and improving the flight economy, the aircraft also reduces the wake vortex strength and reduces the wake vortex safety interval. Through the fitting research on the low speed polar curve of the aircraft after the installation of the wingtip, the change of the induced resistance is analyzed, and then the equivalent aspect ratio is proposed to reflect the influence of the wingtip on the wake vortex intensity. Then taking the aerodynamic raw data of B737-800 and B737-800W aircraft as an example, the calculation and analysis are carried out. The results show that the drag coefficient of the aircraft with wingtip is reduced by about 3% during the take-off and landing phase, which is equivalent to an increase of 4.96% in the aspect ratio of the aircraft, so that the initial strength of the tail vortex can be reduced by 4.73% , So that the inducing torque coefficient of the rear machine under the same weather conditions is reduced by about 6% -8%, and the safety margin of the tail vortex can be reduced by about 3.5%.