大攻角试验半经验壁压信息洞壁干扰修正方法  

ON A SEMIEMPIRICAL WALL PRESSURE SIONATURE CORRECTION METHOD FOR HIGH ANGLE OF ATTACK MODEL TESTS

作　　者：江桂清[1] 

机构地区：[1]中国空气动力研究与发展中心

出　　处：《航空学报》1994年第8期971-974,共4页Acta Aeronautica et Astronautica Sinica

摘　　要：提出用壁压信息洞壁干扰修正法，确定出大攻角典型试验状态的半经验修正系数，用它修正外形近似的模型大攻角试验其它状态的洞壁干扰。这样，模型大攻角试验的洞壁干扰修正既能接近壁压信息修正法的准确结果，又能如半经验修正方法那样简便。经两组模型试验数据验证，结果满意。A wall pressure signature correction method is developed to detennine the semiempirical correction factors suitable to the similar geometric model in a typical test attitude,in order to correct the wall interference on the model in other tested attitudes with a high angle of attack.In this way the correction procedure for the high angle of attack model tested is as easy and convenient as a semiempirical method,meanwhile it remains accurate enough comparing to the standard wall pressure signature method.The demonstrations with two sets of models pres-ented indicate good results.

关 键 词：风洞 壁面压力 洞壁干扰 歼击机 

分 类 号：V211.71[航空宇航科学与技术—航空宇航推进理论与工程]