飞机进气道出口边界层测量试验与数值计算  

Flight Measure Test and Numerical Analyses for Boundary Layer of Airplane Inlet Exit

作　　者：高颖[1] 赵海刚[1] 吕伟[1] 刘海荣[1] 廖小文[1] 

机构地区：[1]中国航空工业集团公司中国飞行试验研究院,陕西西安710089

出　　处：《工程与试验》2015年第1期30-33,89,共5页Engineering and Test

摘　　要：基于某飞机科研试飞,进行了飞机进气道出口边界层测量试验系统设计与搭建,完成了发动机工作在多种状态下的边界层测量。通过建立三维数值计算模型,进行了与试验对应工况下的边界层特性计算。计算结果和试验数据吻合性良好,误差较小。分析结果表明,随着发动机状态逐渐增大,进气道出口处的物理边界层厚度相应增大,位移边界层厚度减小,边界层对空气流量的影响逐渐降低。The measurement system for boundary layer at the inlet exit is designed and built based on the flight test. Boundary layer measurement is done in different engine conditions in the flight test. The model of 3D numerical calculation for the boundary layer characteristic in the same conditions with the test is established. The numerical calculation results are in agreement with the test data and the error is acceptable. By analyzing the results, it is shown that with the increasing of aeroengine Nlh, the geometric thickness of boundary layer is increasing while the momentum thickness of boundary layer is decreasing, and the affect of boundary layer on the flow is reduced.

关 键 词：飞机进气道 飞行试验 边界层厚度 数值计算 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]