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一个GBU—15导弹模型系列在NASA的艾姆斯航空实验室的6英尺超音速风洞和14英尺跨音速风洞中进行了试验;该试验对十字型导流片—弹翼外形在大攻角下的诱导滚转力矩进行了测定。试验的马赫数从0.65变到2.0,而攻角达到35°。对30种不同外形作了试验。外形的变化包括导流片的不同翼展、翼弦、后掠角、导流片——弹翼的间距及其组合形式以及头部钝度等。滚转对外形变化的灵敏度可在平衡舵偏角的项内确定。最大的滚转力矩发生在0.9马赫数的时候。平衡最大的攻角能力为马赫数和外形变化的函数。
A series of GBU-15 missile models were tested at 6-foot supersonic wind tunnels and 14-foot transonic wind tunnels at NASA's Ames Aerospace Laboratory. The test was conducted on cruciform baffles - Angle of the induced tumbling torque were measured. The Mach number changed from 0.65 to 2.0 and the angle of attack reached 35 °. Thirty different shapes were tested. Changes in shape include diversion wings of different wingspan, chord, sweepback angle, the distance between the guide piece - wing and its combination of form and head dullness. The sensitivity of the rollover to the change in shape can be determined in terms of the balance of the steering angle. The maximum roll moment occurs at Mach 0.9. The ability to balance the maximum angle of attack is a function of the Mach number and shape change.