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当飞机航向失稳时,垂尾所在的机身后体处于低能的翼身涡尾流中,效率降低,而机身前体则位于尚未干扰的气流中,在机身头部加前体边条,可以起到增加航向静稳定性作用。通过对一系列前体边条的试验研究,发现长度为机身总长3%的前体边条,可将全机航向失稳迎角提高约8°左右,且侧滑角越小,航向失稳迎角提高越多。通过测压和PIV试验数据可以发现,前体边条提高航向静稳定性,主要是由于前体边条产生边条涡,该涡主要影响机身前体,使得前体背风侧负压力值减小,从而导致前体截面不稳定偏航力矩减小,增加了全机的航向静稳定性。
When the aircraft heading is unstable, the rear fuselage where the vertical tail is located is in a low energy wing vortex wake, the efficiency is reduced, while the fuselage precursor is located in the air flow has not yet been interrupted, the fuselage plus the precursor edge Article, you can play to increase the role of static stability. Through a series of experiments on precursor strip, it is found that the frontier strip with length of 3% of the total length of the fuselage can increase the heading angle of the whole machine heading to about 8 ° and the smaller the side slip angle, the heading loss Steady angle of attack to improve more. Through the pressure measurement and PIV test data, it can be found that the edge of the precursor improves the heading stability, mainly due to the edge vortex generated by the precursor edge strip, which mainly affects the fuselage precursor so that the negative pressure on the leeward side decreases Small, resulting in unstable precursor cross-section yaw torque decreases, increasing the aircraft’s heading stability.