The invention belongs to the technical field of aircraft control, and particularly relates to a wing lift line slope determination method, which comprises the following steps: step 1, calculating the characteristic thickness tclim of the wing lift line slope, and determining the thickness types of wings, including thin wings and thick wings; 2, calculating the characteristic Mach number of the wing lift line slope, wherein the characteristic Mach number comprises the characteristic Mach number Max of a thin wing, the first peak value characteristic Mach number Ma1 of a thick wing, the second peak value characteristic Mach number Ma3 of the thick wing and the minimum peak value characteristic Mach number Ma2 of the thick wing; step 3, calculating a body interference influence factor Kb; and step 4, calculating the lift line slope CL alpha w of the wing based on the characteristic Mach number of the wing and the fuselage interference influence factor Kb.
本申请属于飞机操控技术领域,具体涉及一种机翼升力线斜率确定方法,包括:步骤一、计算机翼升力线斜率的特征厚度tclim,确定机翼的厚度类型,包括薄机翼、厚机翼;步骤二、计算机翼升力线斜率的特征马赫数,包括薄机翼的特征马赫数Max、厚机翼的第一次峰值特征马赫数Ma1、厚机翼的第二次峰值特征马赫数Ma3、厚机翼的最小峰值特征马赫数Ma2;步骤三、计算机身干扰影响因子Kb;步骤四、基于机翼的特征马赫数、机身干扰影响因子Kb,计算机翼的升力线斜率CLαw。
Wing lift line slope determination method
一种机翼升力线斜率确定方法
2025-01-10
Patent
Electronic Resource
Chinese
Prediction of Delta Wing Leading-Edge Vortex Circulation and Lift-Curve Slope
Online Contents | 1997
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