CFD辅助高涵道比发动机短舱设计方法研究

A Study of the Design Method of CFD Assisted High Bypass Ratio Engine Nacelles

随着航空宇航技术的研究及应用不断发展,进气道作为高速飞行器的重要组成部分,其性能对高速飞行影响显著。首先建立进气道三维数值计算模型,运用计算流体动力学理论(CFD)计算方法,研究了总压恢复系数随攻角、侧滑角和马赫数等不同工况的变化情况,进而研究各工况下进气道性能,为进气道性能优化、评价和再设计提供了方法和依据。

The inlet is an important part of high-speed aircrafts and with the increasing development of the research and application of aerospace technology, its performance greatly affects the flight of high-speed aircrafts. The paper starts with building three-dimensional numerical calculation model of the inlet, and by the use of calculating method of Computational Fluid Dynamics （CFD）, studies total pressure recovery coefficient＇s changes in various working conditions as to attack angle, sideslip angle and Mach number, and accordingly further studies the inlet performance under various working conditions, so as to provide a method and basis for the performance optimization, assessment and redesign of the inlet.