枭龙飞机Bump进气道设计

Design of Bump Inlet of Thunder/JF-17 Aircraft

对枭龙飞机先进的无隔道超声速进气道（Bump）的设计和风洞试验进行了分析。结果表明：枭龙飞机Bump进气道性能优异,总压恢复系数高,与斜板进气道比,σ提高0.02-0.04;综合畸变指数低,满足进/发匹配要求;并且取消了附面层隔道和放气门系统,使得飞机阻力小、重量轻、可靠性高。

An advanced diverterless supersonic inlet （bump） design and the wind test of the thunder/JF- 17 aircraft are analyzed. The bump inlet has excellent aerodynamic performances ： high total pressure recovery （σ is 0.02-0.04 higher than traditional fixed geometry inlet）, low distortation and good compatibility. The Bump inlet eliminates many traditional complex features associated with boundary layer management： the diverter, bleed system and bypass system. By eliminating these features, the inlet aperture is integrated with the aircraft forebody, thus producing the best value configuration with low drag, low weight and high reliability.