摘要
通过试验的方法,分析在不同来流速度和不同机身攻角状态下各部件对直升机进气道性能的影响,并模拟了进气网罩结冰对进气道性能的影响。结果表明,当来流速度或进气流量增加的时候,总压恢复系数下降,进气畸变减小;偏流片和进气网罩均使进气畸变减小;附面层泄流槽在前飞时能使进气畸变明显减小;进气网罩堵塞使总压恢复系数下降,同时进气畸变减小。通过结果分析,得出了进气道优化设计的建议。
An experimental study of the flow in a helicopter air intake was completed in low speed wind tunnel. The flow performances of the air intake with different parts at different velocities and attack angles were measured and analyzed, and the frozen state of air intake grid was simulated and analyzed. The results indicate that the total pressure recovery coefficient decrease, the distortion de- crease when velocity and the mass flow increase; the distortion decrease observably at the forward flight simulation with the boundary layer bleed; the total pressure recovery coefficient and the distor- tion decrease with the air intake grid or the deflector; the total pressure recovery coefficient decrease but the distortion decrease observably at the frozen state of the air intake grid. Some proposals for the optimization of the air intake were obtained from the conclusions.
出处
《直升机技术》
2013年第1期15-19,25,共6页
Helicopter Technique
关键词
直升机
进气道
总压恢复
畸变
helicopter
air intake
total pressure recovery
distortion
