摘要
基于圆锥-圆台组合平板捕获翼构型,通过改变尾缘展向扩张角,获得一系列不同外形,在典型亚声速(Ma=0.5)来流条件下开展数值计算,并重点分析了机体尾部截面形状和攻角变化对流动特性和气动特性的影响。结果表明:在0°攻角状态下,机体尾截面展向变宽,机体与捕获翼之间的流场区域对来流的扩张减弱,机体圆台上表面的逆压梯度减小,可有效抑制机-翼之间流场内的流动分离现象,同时整机升力系数增大,阻力系数先减小后增大。随攻角增大,机体圆台上表面压力增大,分离区范围逐渐缩小直至消失,机体尾截面展向变宽可加速分离区消失的进程。当攻角进一步增大时,机体背风面出现横向绕流,但机体尾截面展向变宽可以延缓横向绕流的发展。计算结果还表明,随攻角增大整机升力及阻力主要由捕获翼贡献,机体贡献的气动力随攻角变化不敏感,机体尾截面展向变宽对整机焦点位置影响较小。机体下表面几何形状变化对机体与捕获翼之间的区域内流动特性和捕获翼部件的气动力特性无明显影响。
Based on the conceptual configuration combining the conical-cone airframe and flat plate capturing wing configuration,a series of different shapes were obtained by changing the side expansion angle of the trailing edge.The configuration was solved by computational fluid dynamics under the condition of typical subsonic flow(Ma=0.5).The results show that,at the angle of attack of 0°,the spanwise section of the body tail widened,the expansion effect of the channel between the body and the capturing wing on the incoming flow was weakened,and the reverse pressure gradient on the upper surface of the body platform was reduced,which could effectively inhibit the flow separation phenomenon in the channel.In addition,the whole vehicle lift coefficient rose,and the drag coefficient first fell and then grew.With the increase of the angle of attack,the pressure on the upper surface of the round platform of the body climbed,while the range of the separation zone gradually declined until it disappeared.Furthermore,the spanwise widening of the tail section of the body could accelerate the disappearance of the separation zone.When the angle of attack increased further,the transverse flow appeared on the leeward side of the body,while the spanwise widening of the body tail section could delay the development of the transverse flow.As the angle of attack increased,the calculation results also show that the lift and drag of the whole machine were mainly attributed to the capturing wing.The aerodynamic force contributed by the body was not sensitive to the change of the angle of attack.The spanwise widening of the body tail section had little effect on the aerodynamic center of the whole vehicle.The geometry change of the lower surface of the body had no significant effect on the flow characteristics in the channel between the body and the capturing wing and the aerodynamic characteristics of the capturing wing.
作者
王浩祥
肖尧
张凯凯
李广利
常思源
田中伟
崔凯
Haoxiang WANG;Yao XIAO;Kaikai ZHANG;Guangli LI;Siyuan CHANG;Zhongwei TIAN;Kai CUI(State Key Laboratory of High-Temperature Gas Dynamics,Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China;School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China;Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China)
出处
《航空学报》
EI
CAS
CSCD
北大核心
2023年第6期169-185,共17页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(12002347)
中国科学院基础前沿科学研究计划(ZDBS-LY-JSC005)。
关键词
高压捕获翼
亚声速
流动特性
流动分离
尾缘
high-pressure capturing wing
subsonic
flow characteristics
flow separation
trailing edge
