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结合一类似于“全球鹰”的无人侦察机外形 ,对一种新型高隐身低外阻进气道进行了如下设计 :采用背负式布局方案 ,使用无隔道技术 ,并提出了一种新的进口截面形状。加工了风洞试验模型并开展了验证性风洞实验研究工作。结果表明 :(1 )尽管受到机头遮蔽的不利影响 ,且没有采用传统的附面层隔道 ,所给出的背负式无隔道进气道方案性能 (Ma :0 5 0～ 0 70 ,α :- 4°～ 6° ,σ >0 975 )与常规的有隔道“S”弯进气道相当 ;(2 )特殊进口截面形状及无附面层隔道技术的采用将进气道与机身有机地融为一体 ,使进气道整体都处于飞行器头部的遮蔽之中 ,这有利于改善飞行器的阻力特性和隐身性能 ;(3)进气道出口截面上未发现因附面层吸入而造成的低总压区 ,这说明高度与当地附面层厚度相当的进口鼓包能有效地隔除附面层中能量较低的气流 ;(4 )研究范围内 ,负攻角对进气道的总压恢复系数有利 ,正攻角对周向畸变指数有利 ,而侧滑角则对两者均有着不利影响 ;(5 )唇口的设计对进气道的侧滑角性能有着重要影响 ,进气道性能的进一步提高应考虑唇口设计的改进
Combined with the appearance of an unmanned reconnaissance aircraft similar to the Global Hawk, a new type of stealth low external resistance air intake is designed as follows: a knapsack layout scheme is adopted, the laneless technology is used, and a new The import of cross-sectional shape. The wind tunnel test model was processed and the verification wind tunnel experiment was carried out. The results show that: (1) Despite the negative influence of the nose shielding and the absence of the traditional surfacing, the performance of the knapsack-free bayonet inlet (Ma: 0 0 0 0 0 70, α: - 4 ° ~ 6 °, σ> 0 975) is equivalent to the conventional “S” curved inlet duct; (2) And the fuselage organically integrated into the air intake in the head of the overall cover, which is conducive to improving the aircraft’s resistance characteristics and stealth performance; (3) intake port cross section was not found due to attached The results show that the inlet drum with the height corresponding to the thickness of the local cover can effectively separate the low-energy airflow in the cover; (4) In the research area, The total pressure recovery coefficient of the airway is favorable, while the positive angle of attack is favorable for the circumferential distortion index, while the side slip angle has an adverse effect on both. (5) The design of the lip is important for the performance of the side slip angle of the air intake Impact, further improvements in inlet performance should consider lip design improvements