CAJ | 학술논문

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。
채용근거국외공개문헌설계적류CAV모형，재0．6m×0．6m 과/초성속풍동중개전료다체간우여분리망격측력시험연구，초보획득료전형다체비행기분리과정중적기동특성변화규률。시험결과표명，재하모형기동특성수분리위치변화영향비상명현。재하모형연축향분리시，기동력（구）축보접근자유류중기동력（구）치，재하모형법향위치개변회인발기기동력（구）치발생경위극렬적변화。인발저충현상적원인유량개：일시미적화두격파적발전개변료불동축향위치처재하모형적표면류태，종이영향료기기동특성；이시모궤모형저부류동구유명현적비대칭팽창특정，불동법향위치처류속대소화방향차이명현，도치재하모형기동특성수법향위치변화경위극렬。
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.