摘要
Computational fluid dynamics and semi-empiric method were used to study the effect of Diamondback wing geometric parameters on its aerodynamic characteristics. The comparison of calculation and experiment results indicate that this method is accurate for the small and medium angle of attack. The aerofoil NACA64-108 can obviously increase the lift and lift-drag ratio of Diamondback wing. The aerodynamic interference between the front-wing-strip and rear-wing-strip will reduce the lift and increase the drag. The configuration that the front-wing-strip is higher than the rear-wing-strip can reduce the interference between two strips. If the height difference between two strips is 9mm, the aerodynamic interference is minimum, and the lift-drag ratio reaches maximum.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 1048-1052 |
| 页数 | 5 |
| 期刊 | Binggong Xuebao/Acta Armamentarii |
| 卷 | 31 |
| 期 | 8 |
| 出版状态 | 已出版 - 8月 2010 |