舰载机折叠翼气动特性分析

折叠翼技术是舰载机与航母相匹配的关键,研究折叠翼的气动特性对舰载机飞行动态及安全性具有重要意义。基于离散化的思想对折叠翼进行建模,并利用计算流体力学CAE软件Fluent对其进行数值计算,从升力系数和阻力系数变化及压力分布分析舰载机折叠翼的气动特性。结果表明:当折叠角为75°时,外翼的升力系数及侧向力系数将达到最大,阻力系数最小;一旦折叠机构失效,外翼的折叠将导致机翼整体升力系数及阻力系数大幅度下降,气动特性变差;与折叠机构失效前相比,折叠后的机翼失速迎角变小,且在失速后升力系数有缓慢上升趋势。

Aerodynamic characteristics analysis of folding wings of carrier-based aircraft

Folding wing is the key technology to match carrier-based aircraft with aircraft carrier. Research on the aerodynamic characteristics of folding wings is of great significance to the flight dynamics and safety of carrier-based aircraft. Based on the idea of discretization, the folding wing was modeled, and numerical calculation was analyzed by using the computational fluid dynamics CAE software Fluent, and the aerodynamic characteristics of folding wings were analyzed according to the lift coefficient and drag coefficient change and pressure distribution. The results show that when the folding angle is 75°, the lift coefficient and lateral force coefficient of the outer wing reach the maximum, and the drag coefficient is the smallest. Once the folding mechanism fails, the folding of the outer wing causes the overall lift coefficient and drag coefficient of the wing to drop significantly, and the aerodynamic characteristics are degraded. Compared with the folding mechanism before failure, the stalling angle of attack of the wing after folding becomes smaller, and the lift coefficient tends to rise slowly after the stall.