摘要
为根据飞机高/低速风洞测压试验数据给出飞机的机翼、机身和尾翼的气动载荷分布,供外载荷计算使用,介绍了一种基于测压风洞试验的大展弦比飞机气动载荷分布计算方法。通过将测压试验数据插值到载荷计算模型网格中,并将测压试验数据与测力试验数据相协调,再对压力分布数据进行切面/纵向积分、样条插值和线性化拟合后,对飞机活动面中立、偏襟翼、偏副翼、偏方向舵和偏升降舵状态时的机身、短舱、机翼及翼身组合体气动载荷分布进行了计算。总结了各剖面区域表面压力随迎角、侧滑角,以及飞机舵面变化的规律,验证了测压数据与测力数据进行协调的必要性。对飞机气动载荷的设计优化有重要的反馈评估作用。
For providing the aerodynamic load distribution of wing, fuselage and tail for aircraft external load calculation according to the pressure measurement data of aircraft high-speed and low-speed wind tunnel, this paper introduced a calculation method of high-aspect-ratio aircraft aerodynamic-load distribution based on piezometric wind tunnel test.This method interpolates the pressure test data into the load calculation model grid, and coordinates the pressure test data with the force test data.After sectional/longitudinal integration, spline interpolation and linear fitting of the pressure distribution data, the aerodynamic load distribution of the fuselage, nacelle, wing and wind body combination is calculated when the flap, aileron, rudder and elevator is deflected or the aircraft moving surface is in the neutral states.The law of surface pressure variation with angle of attack, sideslip angle and aircraft control surface in each section area is summarized, and the necessity of pressure measurement data coordination is verified.This method plays an important role in feedback evaluation of aircraft aerodynamic load design optimization.
作者
郭天天
刘伟
杨全
GUO Tiantian;LIU Wei;YANG Quan(XAC,Xi’an 710089,China)
出处
《飞机设计》
2023年第1期38-43,共6页
Aircraft Design
关键词
大展弦比
风洞试验
气动载荷分布
外载荷计算
high-aspect-ratio
wind tunnel test
aerodynamic load distribution
external load calculation
