摘要
在非线性迎角范围内，雷诺数通过对机翼脱体涡和前机身体涡影响来改变飞机的纵向气动特性。由于现有风洞条件所限，在这一范围内，使用变雷诺数试验方法把试验数据外插到飞行值非常困难。为解决这一问题，本文给出了一种基于全尺寸飞行前缘雷诺数计算出外露翼可得到的前缘推力系数，并通过风洞试验求出试验条件下机翼上可得到的前缘推力系数，从而获得雷诺数对气动特性影响量的工程计算方法。该方法适用于翼面产生脱体涡流型或脱体涡占优（涡破裂前）所引起的非线性问题。
In the range of the nonlinear angles of attack,the longitudinal aerodynamic characteristics of aircraft is changed because of Reynolds number effects on the wing detached vortex and the front fuselage vortex.Limited by the present wind tunnel conditions,the test method of changing Reynolds number is applied.But it is very difficult to correct the test data to flight values in this range.This paper presents an engineering calculation method of effects of Reynolds number.Based on the leading edge thrust coefficient of exposed wing in the condition of flight leading edge Reynolds number of the full scale aircraft,the testing leading edge thrust coefficient of wing is obtained by the wind tunnel experiment,thus the effect by Reynolds number is obtained.The method is only suitable for the nonlinear problem caused by detached vortex of wing before vortex breakdown.
出处
《流体力学实验与测量》
CSCD
1999年第2期83-89,共7页
Experiments and Measurements in Fluid Mechanics
关键词
雷诺数
后掠角
展弦比
飞机
纵向气动特性
Reynolds number
sweep angle
aspect ratio
aircraft
longitudinal aerodynamic characteristics
engineering calculation method
