摘要
本文通过测力和水槽流态观察试验研究了战斗机和导弹式的翼体组合体翼涡破裂的推迟措施。利用安置于机翼(弹翼)前方和机体两侧的大后掠、小面积的机体边条所产生的边条涡的有利干扰,可以有效地推迟翼涡的破裂,从而达到提高最大升力系数和临界迎角的目的,试验表明,安置在不同位置的机体边条均可不同程度地提高最大升力系数C_(Lmax),在适当位置时,可提高临界迎角α_(kp)达2°～3°。
An experimental investigation to delay wing vortex bursting for fighter and missile-type wing-body combination was carried out by means of flow visualizations and force measurements. Both wings of the experimental models had sharp leading-edge. The body-strake with high sweepback and small area was fixed to both sides of the body. The fighter-type model had a delta body-strake with 70 deg. sweepback angle, 10.2% of the exposed wing span and 2.2% of the exposed wing area. There were three strake positions along the vertical direction of the body, i.e. the higher position, the middle one and the lower one. The vortex flow pattern visualization of models with and without body strake are presented in the paper. The comparison of these flow patterns indicates that the vortex bursting of the wing for model with body-strake is delayed efficiently. Longitudinal force and moment data were obtained for the fighter model and comparison between experimental results with and without body-strake were given graphically. It illus trates that the effect of the body-strake can increase actually the maximum lift coefficient and that to some extent the critical angle of attack.Experimental result also shows that the drag coefficient has some increment in the presence of body-strake over the range of angle of attack; when a<10°, the lift-drag ratio is decreased, but a>°, the body-strake has not effect essentially on lift-drag ratio. As using the body-strake, the longitudinal static stability must be considered, be-cause it is decreased.
出处
《空气动力学学报》
CSCD
北大核心
1992年第1期53-59,共7页
Acta Aerodynamica Sinica
关键词
大迎角
分离流
涡破裂
流态显示
high angle of attack, seperation flow, vortex bursting, flow visualization, force measurement
