1种宽马赫数二元超声速进气道性能快速计算方法  

A Fast Calculation Method for the Performance of a 2-D Supersonic Inlet with Wide Mach Number

作　　者：刘雨 王定奇 谢旅荣[2] LIU Yu;WANG Ding-qi;XIE Lyu-rong(Chinese Flight Test Establishment,Xi'an 710089,China;College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]中国飞行试验研究院,西安710089 [2]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空发动机》2020年第5期34-39,共6页Aeroengine

基　　金：航空动力基础研究项目资助。

摘　　要：为了在设计过程中快速估算二元超声速进气道性能,通过对二元超声速进气道内流场结构进行分析,基于斜激波、膨胀波公式及流量连续方程等理论提出了二元超声速进气道性能快速计算方法,并对其进行黏性修正。为验证方法的准确性,对1个工作马赫数范围为2.5~4.5,设计马赫数为3.7的定几何二元进气道进行数值仿真。结果表明:仿真结果与快速计算结果对比误差在5%以内。该方法可以用来快速计算宽马赫数二元超声速进气道的临界总压恢复系数、流量系数及喉道马赫数等性能参数;在计算进气道超临界性能时具有一定的准确性;该方法也适用于变几何二元进气道的初步选型设计及性能计算。In order to quickly estimate the performance of a 2-D supersonic inlet in the process of design,according to analyzing the structure of the internal flow field in the 2-D supersonic inlet,a fast calculation method for the performance of a 2-D supersonic inlet was proposed based on the theory of oblique shock,expansion wave formula and flow continuity equation and its viscosity was modified.A fixed geometry 2-D inlet with a working Mach number range of 2.5~4.5 and a design Mach number of 3.7 was numerical simulated to verify the accuracy of the method.The results show that the comparison error between simulation results and fast calculation results is less than 5%.The method can be used to quickly calculate the critical total pressure recovery coefficient,flow rate coefficient and throat Mach number of the 2-D supersonic inlet with wide Mach number.The method has certain accuracy in calculating supercritical performance of inlet and is also suitable for the preliminary selection design and performance calculation of variable geometry 2-D inlet.

关 键 词：二元进气道 宽马赫数 变几何进气道 快速计算方法 性能参数预测 航空发动机 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]