0.6m连续式跨声速风洞槽壁试验段数值模拟

Numerical evaluation of aerodynamic design of slotted test section in 0.6m closed-circuit transonic wind tunnel

为验证0.6m×0.6m连续式跨声速风洞开槽试验段设计方案和流场指标实现程度,通过数值模拟对试验段高亚声速和低超声速流场特性进行了研究,将全槽与半槽方案进行了对比。计算表明:当前气动设计方案较为合理,试验段均匀区长度、流场偏角能够达到设计要求。在高亚声速条件下,半槽方案更优;通过抽气可以建立低超声速流场,抽气量过大时会降低试验段马赫数均匀区长度,使用全槽方案时试验段对驻室的扰动更小。对再入调节片附近的流场分析表明,开槽附近的流动具有明显的非定常特征。

Computational fluid dynamics （CFD） gradually plays an important role in the evaluation of the wind tunnel design project. This paper is about the evaluation results of the slotted test section of 0.6m × 0.6m continuous transonic wind tunnel including alternative design and flow field quality, especially comparing full slot with half slot. It presents the control equations and boundary conditions for numerical simulation firstly. Then the details of numerical results about the high subsonic and low supersonic flow characteristic are given. The length of velocity uniformity region and velocity deflection angle meet the design accuracy and that proved the rationality. The half slot project was better than the full one at high subsonic. Low supersonic field could be achieved when air was bleed from plenum chamber. However, more bleed air rate, shorter length of velocity uniformity region. Full slot project had less disorder on flow of the plenum chamber than the half. Further investigation on the flow mechanism of re-entry flaps indicated that the flow was unsteady one significantly.