可调叶片推力矢量转向对气动特性影响的研究  

An Investigation on the Characteristics of Thrust Vectoring Using Turning Vanes for a Fighter Configuration

作　　者：秦燕华[1] 洗礼敏 

机构地区：[1]北京航空航天大学,北京100083 [2]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》1997年第3期276-283,共8页Acta Aerodynamica Sinica

摘　　要：为了研究可调叶片推力转向对大攻角纵横向气动特性的影响，利用某战斗机的1∶11模型对可调叶片的偏角、长宽比及纵向位置的影响进行了风洞试验研究。试验是在中国空气动力研究与发展中心低速空气动力研究所的Φ3．2m低速风洞中进行的。试验风速为60m／s，相应的Re数为2．1×106，喷流落压比为2．11，攻角范围为－4°～48°。本文给出了主要试验结果并对结果进行了简要的讨论。An experimental investigation has been conducted to determine the characteristics of thrust vectoring using turning vanes installed at the exit of nozzle for a fighter configuration with 60° delta wing in the CARDC Φ3.2m diameter low speed wind tunnel over an angle of attack range of -4°~48°. During the experiment, effects of the area,longitudinal position and deflection of the vane were measured at a pressure ratio of 2.11 and Reynolds number of 2.1×106.Some typical results obtained from the experiment are presented in the paper. It is shown that thrust vectoring due to longitudinal and lateral turning vanes has significant effects on the pitch ing and yawing moment over a large ang1e of attack range, respectively, whereas has a little effects on the slope of pitching moment and yawing moment curve, which supposed that thrust vectoring using turning yane is an effective measure to provide moments needed to control the aircraft in manoeuvering at high angles of attack.

关 键 词：可调叶片 大攻角气动力 风洞 气动布局 战斗机 

分 类 号：V212.11[航空宇航科学与技术—航空宇航推进理论与工程] V274.41