The invention discloses a high-lift airfoil design method, a high-lift airfoil and an aircraft, and relates to the technical field of aerodynamic configuration design, and the high-lift airfoil design method comprises the following steps: S1, extending from a wing root chord leading edge point in an airfoil design plane according to a set sweep-forward angle until the wing root chord leading edge point intersects with a precursor shock wave surface to form a sweep-forward angle chord; s2, the intersection point of the sweepforward angle chord and the front body shock wave face extends backwards for a set length along the front body shock wave face, and a sweepback angle chord is formed. And S3, a wingtip chord parallel to the wing root chord is arranged at the other end of the sweepback chord, and the length of the wing root chord and the length of the wingtip chord are determined according to the designed wing area. The problem that in the prior art, a triangular airfoil or a trapezoidal airfoil is adopted, and a larger airfoil area is needed for obtaining larger lift force is solved.
本发明公开了一种增升翼面设计方法及增升翼面及飞行器,涉及气动外形设计技术领域,该增升翼面设计方法包括以下步骤:S1:在翼面设计平面内从翼根弦前缘点按设定前掠角延伸,直至与前体激波面相交,形成前掠角弦。S2:在前掠角弦与前体激波面交点处沿前体激波面向后延伸设定长度,形成后掠角弦。S3:在后掠角弦另一端设置与翼根弦平行的翼梢弦,并根据设计翼面积,确定翼根弦和翼梢弦的长度。解决了现有技术中采用三角形翼面或梯形翼面,存在为了获取更大的升力,需要更大的翼面积的问题。
High lift airfoil design method, high lift airfoil and aircraft
一种增升翼面设计方法及增升翼面及飞行器
2023-11-17
Patent
Electronic Resource
Chinese
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