大后掠翼大迎角定常与非定常俯仰气动特性及其控制

 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 2S 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。

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

Experiments were conducted to investigate the aerodynamic characteristics of a74 degree swept deltaw ing model equipped w ith an apex flap s and leadingedge vo rtex2flap s under thecondit ions of steady state w ith the angle of at tack varying from 0°to 90°and the unsteady p itch ingstate w ith the frequencies 0. 4, 0. 8 and 1. Hz asw ell as the effects of flow cont ro l via flap deflect ion. Comparisons betw een the results go t from experiments and the computat ion by so lving N Sequat ions w ere made. The unsteady p itch ing mo t ion caused the hysteret ic variat ion of the aerodynam ic coefficients to occur; how ever the advantageous effects of flap cont ro lw ere basically kep t asin the steady state. Experimental results such as the liftcoefficients obtained from the calibrat iontests of the basic delta w ing w ith no flap s w ere comparable to the co rresponding values found inreferences, and thus enhanced the reliability of the p resent tests.