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通过风洞实验数据对比分析了4种布局形式下超声速飞行器进气道的速度特性、迎角特性和侧滑角特性,所研究的进气道布局形式包括轴对称进气道、下颔式进气道、双下侧二元进气道以及“X”型倒置二元进气道,且均为定几何混压式进气道。结果表明:(1)4种布局形式进气道性能随马赫数的变化趋势基本一致,唯有“X”型倒置二元进气道的流量系数在封口马赫数达到1后略有下降;(2)在实验范围内,下颔式进气道和双下侧二元进气道均具有良好的正迎角性能,其中以双下侧二元进气道正迎角性能最好,但是负迎角性能都较差,轴对称进气道和“X”型倒置二元进气道在6°迎角以内随迎角增加性能虽有减小,但总的来说下降不大,然而当迎角大于6°时,性能急剧降低;(3)在小侧滑角4°以内,轴对称进气道、下颔式进气道和“X”型倒置二元进气道性能均下降不大,而双下侧二元进气道则相对较差。
Through the experimental data of wind tunnel, the velocity characteristics, the angle of attack characteristics and the side slip angle characteristics of the inlet of the supersonic aircraft under the four kinds of layout are compared and analyzed. The inlet layout studied includes the axisymmetric inlet, Air way, double bottom two way air inlet and “X” type inverted two way air way, all of them are fixed geometry mixed pressure type inlet way. The results show that: (1) The performance of four kinds of layout air intakes are almost the same with Mach number, only the flow coefficient of “X” inverted binary inlet slightly decreases after the sealing Mach number reaches 1 ; (2) In the experimental range, both the lower air inlet and the double lower air inlet have a good positive angle of attack performance, of which the double lower air inlet has the best positive angle of attack capability, However, the negative angle of attack performance is poor, axisymmetric inlet and “X” -type inverted binary inlet within 6 ° angle of attack with the angle of attack to increase the performance though reduced, but in general does not decline However, when the angle of attack is greater than 6 °, the performance is drastically reduced. (3) Within 4 ° of the small side-to-side slip angle, the axisymmetric intake port, the downwind intake port and the “X” Airway performance are not decreased significantly, while the double under the dual inlet is relatively poor.