碟形升力体流场数值模拟分析

Saucer-Shaped Lifting Body Flow Field Numerical Simulation

为了获得碟形升力体的流场特征和发展规律,以风洞试验数据为验证,通过数值模拟的方法分析了碟形升力体的流场特性和发展规律,同时也对它的失速特性进行了研究.结果表明,碟形升力体流场具有稳定的涡系结构,涡升力对碟形升力体升力的贡献明显,且随迎角增大而增大,4°迎角时涡升力占总升力的8%,40°迎角时涡升力占总升力的30%.碟形升力体的失速迎角达到了40°,优于常规飞机.

In order to obtain the saucer-shaped lifting body＇ s flow filed features and development law, the computational fluid dynamics method was taken to simulate the saucer-shaped lifting body＇ s flow field, as well as its stalling characteristics. The simulation was validated by the wind tunnel experiments. The simulation resuits show that the saucer-shaped lifting body＇ s flow field has a steady vortex structure, bring a significant vortex lift, which increases with the increasing of attack angle. The vortex lift to total lift ratio is 8% when the at- tack angle is 4°, and the ratio is 30% when the attack angle is 40°. The stalling angle of the saucer-shaped lifting body is 40°, which is better than the conventional aircraft.