一种小型超音速风洞技术研究

详细介绍了小型超音速风洞装置的基本结构、工作原理和技术特性。该风洞装置可完成马赫数范围为2～7的空气动力实验。主要进行超音速气流的马赫数、滞止压力、滞止温度、气体流量以及空气动力载荷的测量；还可以观测并研究气流以不同马赫数在模型表面形成的激波、边界层分离和附面层情况等，并可在计算机上形成连续图像。该风洞广泛应用于空气动力、武器弹药工程和航空航天等方面的科学研究。

Techniques of a Small-scaled Supersonic Air Wind Tunnel

It was detailed to introduce the basic structures, operating principles and the technical characteristic of a small- scaled supersonic wind tunnel equipment. It can complete air motive experiment under the condition where the Mach number scope is between 2 and 7. Mainly it can measure the Mach number, stagnation pressure, stagnation temperature, air flow and aerodynamic test of the supersonic speed air current; can also look into and study the shock wave, boundary layer separation and boundary layer etc the air current with the different Mach number forms in the model surface and can form continuous picture on the computer. It can widely be apply to the science research that relates aerodynamics, ammunition engineering and the aviation aerospace etc.