摘要
应用数值方法模拟了飞行器升力面下表面喷气的增升作用。数值模拟的出发方程是Ｎ－Ｓ方程，格式为Ｂｅａｍ－Ｗａｒｍｉｎｇ格式的改进型。模拟结果表明：喷气增升主要是通过改变上、下翼面的压力分布实现的。在一定范围内升力随气流出口速度增加而加大，气流出口速度超过一定值后升力开始下降。喷口位置后移增升效果较好。单一增大气流出口压力时增升效果无明显变化。
The aerodynamic characteristics of an airfoil with a jet issuing from its lower surface are investigated by numerical method.The Navier-Stokes equations are solved using Beam-Warming scheme,By the numerical experiment of different jet parameters,some important characteristics are obtained.Jet can increase the lift of an。airfoil within some range of jet velocity,but beyond this velocity range the lift decrease,with jet location near to the trailing edge of the airfoil,the increase lift effect of jet is more efficient.The lift does not depend on the variation of jet pressure closely.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1994年第5期604-606,共3页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金青年基金
关键词
射流
增升
数值分析
翼型
jet flow,lift augmentation,numerical analysis
