超燃冲压发动机尾喷管性能对型面参数的回归研究  

Regression study of scramjet nozzle performance on contour parameters

作　　者：张文电[1] 王一白[1] 刘宇[1] 覃粒子[1] 张晓源[1] 何淼生[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《航空动力学报》2013年第9期2029-2036,共8页Journal of Aerospace Power

摘　　要：为了研究型面参数对基于三次曲线构型的超燃冲压发动机尾喷管性能的影响规律,采用均匀设计和回归分析的方法开展了型面参数化研究,得到了尾喷管性能参数与构型参数间的回归模型.研究表明下壁面高度对尾喷管的升力性能影响不显著,其余型面参数对尾喷管性能有影响且为交互作用.同时,上下壁面出口高度增加能提高尾喷管推力性能,上壁面长度增加对升力性能有益,而上壁面出口高度和角度的增加则反之;上壁面出口高度对俯仰力矩性能的影响与升力性能类似,但俯仰力矩性能与上壁面入口角度呈正相关,而出口角度在大部分情况下对俯仰力矩性能呈负相关;下壁面在一定范围内截短对上壁面压强分布影响不显著.In order to study the influence rules of contour parameters on the performance of cubic curve shaped scramjet nozzle,contour parametric study was conducted by introducing methods of uniform design and regression analysis,and the regression model of scramjet nozzle performance with contour parameter was obtained.The results show that most contour parameters have interactive influence on nozzle performance,but the influence of lower wall height on nozzle lift characteristic could be neglected.Meanwhile,the thrust performance could be improved with the increase of the lower and upper wall exit height.Upper wall length has positive influence on lift performance,contrary to upper wall exit height and angle.The upper wall exit height＇s correlation with pitch moment performance is similar to lift.The upper wall inlet angle has positive correlation with pitch moment performance while outlet angle has negative correlation in most situations.And within certain range of lower wall＇s curtailment,it has no significant effect on upper wall pressure distribution.

关 键 词：超燃冲压发动机 尾喷管 均匀设计 回归研究 参数化研究 

分 类 号：V235.2[航空宇航科学与技术—航空宇航推进理论与工程]