阻力精确分解的方法研究与数值模拟

根据阻力产生的物理机理将阻力分解为近场阻力和中场阻力,建立实现了阻力精确分解方法:近场阻力法和中场阻力法,前者对飞行器表面压强和切应力积分将阻力分解为压差阻力和摩擦阻力,后者通过区域划分式积分将阻力分解为波阻、粘阻、诱导阻力和数值耗散阻力.选取RAE2822翼型、M6机翼和某宽体标模进行数值模拟,验证阻力分解方法的正确性,对比两种方法进行阻力分解辨识的能力与不足.研究结果表明,中场阻力法可以给出详细的阻力构成,更有利于进行阻力产生分析和减阻优化设计;近场阻力和中场阻力计算可以很好地达到阻力平衡,但由于消除了数值耗散阻力,中场阻力法的计算结果要比近场阻力法更接近实验值.

Method Study and Numerical Simulation of Drag Finer Decomposition

Drag is decomposed into near-field drag and mid-field drag,according to the physical mechanism of drag production.Near-field drag method and mid-field drag method are established fully.The near-field drag method can decompose total drag into drag components such as pressure drag and friction drag.This mid-field drag method can decompose total drag into drag components such as wave,profile,induced and spurious drag.The methods are validated effectively and compared detailedly,depending on RAE2822,M6 and wide-body civil aircraft.The result indicates that the drag components can be showed clearly with the mid-field drag method.Therefore,the mid-field drag method is benefit for understanding of drag generation and drag reduction.In addition,the near-field drag and the mid-field drag can sustain equilibrium with the two methods.Because the mid-field drag method can eliminate numerical error effectively,the result generated by this method fits better to the experiment results than the near-field drag method.