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在1.2m量级亚跨超声速风洞对某型飞机机头模型进行了DPIV高速选型实验,通过实验获得了两个机头模型的流场特性。实验结果表明:在巡航马赫数条件下,机头顶端速度分布平滑,不存在流动分离和超声速区;在快速巡航马赫数条件下,机头顶端存在局部很小区域的超声速区,强度很小,不存在流动分离。实验数据符合气动规律,实验数据可以作为机头气动设计的依据。
In a sub-span supersonic wind tunnel of the order of 1.2m, a DPIV high-speed model selection experiment was conducted on a nose model of a certain aircraft. The flow field characteristics of the two nose models were obtained experimentally. The experimental results show that under the condition of cruise Mach number, the head velocity distribution is smooth and there is no flow separation and supersonic zone. Under the conditions of fast cruise Mach number, there is a small supersonic zone in the tip of the nose, There is no flow separation. Experimental data in line with the laws of aerodynamics, experimental data can be used as the basis of the nose pneumatic design.