摘要:
采用根据国外公开文献设计的类CAV模型,在0.6m×0.6m 跨/超声速风洞中开展了多体干扰与分离网格测力试验研究,初步获得了典型多体飞行器分离过程中的气动特性变化规律。试验结果表明,载荷模型气动特性受分离位置变化影响非常明显。载荷模型沿轴向分离时,气动力(矩)逐步接近自由流中气动力(矩)值,载荷模型法向位置改变会引发其气动力(矩)值发生更为剧烈的变化。引发这种现象的原因有两个:一是尾迹和头激波的发展改变了不同轴向位置处载荷模型的表面流态,从而影响了其气动特性;二是母机模型底部流动具有明显的非对称膨胀特征,不同法向位置处流速大小和方向差异明显,导致载荷模型气动特性随法向位置变化更为剧烈。
Abstract:
A set of quasi CAV model composed of a external model and a internal model was designed according to foreign public documents,and it was used to study the multi-body interfer-ence during separating by grid force measurement at 0.6m×0.6m transonic/supersonic wind tu-unel.The results show that the aerodynamic characteristcs of the internal model would change dramatically during the separation.While the internal model is leaving the external model along the axis,its aerodynamic characteristcs develops towards the value in free stream.Furthermore, dramatical change of its aerodynamic characteristcs will be induced due to the normal location changing.Two factors induced this dramatic change of the aerodynamic characteristcs.The first comes from the unbalance development of wake flow and the head shock wave during the internal model moving from the wake flow region to free stream flow region,which changes the flow structure of the internal model.And the second comes from the change of local velocity induced by the asymmetric base flow expansion,which induces the more dramatic change of the aerody-namic characteristcs.
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