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一种变内流量的侧面进气道的外阻实验结果被提了出来。在亚音速情况下,整流罩前缘半径对满流工作状态的进气道外阻是有影响的,但它的影响随入口流量的减少而减弱。相反,整流罩的外形对溢流阻力的影响却很大,而对满流阻力没有什么影响。对于一个典型的矩形超音速进气道来说,附加的后掠唇口对满流阻力和溢流阻力均有影响。把随压缩面几何尺寸(即中心锥锥角——译者注)而变化的满流阻力和考虑到激波图形不同的预先估算的满流阻力作了比较。对于超音速进气道,其溢流阻力大体上是按预算结果而变的,但对皮托管式进气道,当 M=2.0,计算值大于实验值。这种收益可以认为是由于进气道入口激波和机身附面层的相互作用的结果。综合测量和计算结果之后,得出了一种简单楔形附面层挡板和满流状态的双进气道的压阻。这分报告就是要把实验值和单一的皮托管式进气道的计算结果作一比较。
An experimental result of the external resistance of a variable inlet side inlet is presented. At subsonic speeds, the radius of the cowl front has an effect on the external resistance of the port at full flow, but its effect diminishes as the inlet flow decreases. In contrast, the shape of the fairing has a great influence on the flow resistance but has no effect on the flow resistance. For a typical rectangular supersonic inlet, the additional swept lip has an effect on both full flow resistance and over flow resistance. The full flow resistance, which varies with the geometry of the compression surface, is compared with the previously estimated full flow resistance, which is different from the shock pattern. For supersonic inlets, the relief resistance is largely based on budgetary results, but for Pitot tube intake, when M = 2.0, the calculated value is greater than the experimental value. This gain can be attributed to the interaction of the inlet shock and fuselage cladding. After the comprehensive measurement and calculation results, the piezoresistive of a simple tapered waffle baffle and double inlet with full flow condition is obtained. This sub-report is a comparison of the experimental results with those of a single Pitot tube inlet.