大飞机布局模型跨声速风洞实验尾支撑干扰研究

Study on the rear sting support interference for large transports configuration model in transonic wind tunnel

对某大飞机布局风洞实验尾支撑干扰开展了数值模拟和实验研究,发展的数值方法计算结果与风洞实验结果有很好的一致性。对于类似构型的飞机,在迎角-2°～6°范围,可认为尾支撑干扰量随迎角呈线性变化,采用前位叶片支撑作为辅助支撑带来的二次干扰量可以忽略,新型双天平辅助支撑系统试验进一步验证了这一结果;尾支撑对机身、尾翼、机翼等部件的绕流都有影响,干扰量随构型而变,对阻力、力矩影响较大,且随Ma数变化,因此不同构型实验数据需要单独修正。所发展的带风洞支撑系统的数值模拟软件能够满足工程应用要求,可用于支撑干扰修正研究以及风洞实验支撑系统优化设计。

This article focus on the rear sting support interference of large transport configuration model in a transonic wind tunnel.The CFD and experiment results indicate the same principle for data correction.For the similar configuration model,the rear sting support interference is linear with angles of attack in the range of-2° to 6°.The adjunctive interference of belly vane support is small enough to be neglected in the range of-2° to 6°.The test dada gained from a new twin-balance support system prove it again besides the CFD results.The rear sting affects the flow around the body,the empennage and the wing of the plane.The effect differs with Mach numbers and configurations,especially for drag and pitching moment characteristics.The new developed software for wind tunnel support simulation can be used for test data correction and support optimization during test plan designing in wind tunnels.