Wind tunnel test technique of continuous varying Mach number for air-breathing vehicle
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摘要: 为研究吸气式飞行器加/减速引起的进气道起动/再起动现象，以及该过程导致的飞行器整体气动性能突变问题，基于二维楔面激波机理，在1.2 m量级风洞开展超声速连续变马赫数试验技术研究，通过研制激波发生与控制系统，实现了一次风洞试验过程中马赫数连续可调。该技术方案具有马赫数调节简单、响应快，马赫数控制可靠、精度高等特点。流场校测表明，瞬时变马赫数区域流场品质满足国军标要求，可开展基于马赫数连续变化的测力测压等风洞试验。通过进气道动态特性验证试验，成功捕获了连续减速状态下进气道由起动到不起动的动态过程，临界状态特性与仿真结果一致性较高，该试验技术可为超声速吸气式飞行器进气道及整体气动性能的预测与研究提供有力支撑。Abstract: To study the start/unstart phenomenon of the air-breathing vehicle inlet caused by acceleration or deceleration, which also bring the problem of aerodynamic mutation on vehicle, the test technique of continuous varying Mach number was performed in the 1.2 m supersonic wind tunnel based on the flow mechanism of the 2D wedge shock wave. By developing the shock wave generator system, continuous varying Mach number was realized successfully in one wind tunnel test process. And it has also been confirmed that the technical method can make Mach number vary simply and quickly with high quality and precision. Through the flow-field calibration, the quality of the instantaneous flow-field in variable Mach number region meets the standards of GJB eligibly, and thus the field can be used for force and pressure test compliantly. In addition, the test of inlet starting characteristics was carried out and the dynamic process and critical state from start to unstart were captured, which indicates that the test results agree with the numerical simulation accurately. The test technique could provide effective support for supersonic air-breathing vehicle in aerodynamic performance prediction and study.
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图 17 不同马赫数变化速率下内流道压力脉动特性
Figure 17. Characteristics of dynamic pressure with different rates of varying Mach number at internal flowpath
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