大后掠翼大迎角定常与非定常俯仰气动特性及其控制  

AERODYNAMIC CHARACTERISTICS OF A HIGHLY SWEPT WING IN STEADY/UNSTEADY PITCHING STATES AND EFFECT OF FLAP CONTROL AT LARGE INCIDENCE

作　　者：忻鼎定[1] 余光志[2] 袁礼[3] 

机构地区：[1]北京航空航天大学流体力学研究所 [2]北京大学力学系 [3]中国科学院力学研究所

出　　处：《航空学报》1997年第2期129-134,共6页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金

摘　　要：对装有“前端襟翼”和“前缘襟翼”的７４°后掠三角翼，在迎角０°～９０°范围的定常和非定常（俯仰振动，ｆ＝０．４，０．８，１．２Ｈｚ）的空气动力特性以及襟翼的控制作用作了实验研究。定常流的实验结果与解Ｎ－Ｓ方程的计算结果作了比较。非定常俯仰振动使气动特性的变化出现迟滞现象，但仍能保持襟翼对定常流控制所具有的优越性。不装襟翼的三角翼的部分校测结果与文献中相应数据一致，表明实验结果可信。Experiments were conducted to investigate the aerodynamic characteristics of a 74 degree swept delta wing model equipped with an apex flaps and leading edge vortex flaps under the conditions of steady state with the angle of attack varying from 0° to 90° and the unsteady pitching state with the frequencies 0.4, 0.8 and 1.2Hz as well as the effects of flow control via flap deflection. Comparisons between the results got from experiments and the computation by solving N S equations were made. The unsteady pitching motion caused the hysteretic variation of the aerodynamic coefficients to occur; however the advantageous effects of flap control were basically kept as in the steady state. Experimental results such as the lift coefficients obtained from the calibration tests of the basic delta wing with no flaps were comparable to the corresponding values found in references, and thus enhanced the reliability of the present tests.

关 键 词：定常 非定常流 大迎角 襟翼控制 机翼 

分 类 号：V211.15[航空宇航科学与技术—航空宇航推进理论与工程] V224