Developing and applying Mach 4.5 nozzle in hypersonic wind tunnel

高超声速风洞马赫数4.5喷管研制与应用

China Aerodynamics Research and Development Center, Mianyang 621000, China

Received: 4 January 2021

Abstract

Mach 4.5 tests in a conventional trans-supersonic wind tunnel are often accompanied by the air liquefaction phenomenon, resulting in the low reliability of test data. The Mach 4.5 nozzle developed in a hypersonic wind tunnel is able to heat airflow and provide more accurate test data. At present, China does not have the capability to test the Mach 4.5 nozzle in the 0.5-meter hypersonic wind tunnel. This gap may be filled by developing the Mach 4.5 nozzle in the hypersonic wind tunnel. The axisymmetric nozzle profile was calculated by the inviscid flow calculation method, and the boundary layer was modified by the Sivells-Payne method. Then, the numerical simulation was carried out, and the simulation results prove that the nozzle profile thus calculated meets the design requirements of the Mach number. For its structural design, a three-section design method is adopted to ensure the continuity and smoothness of the inner surface so as to better calibrate the flow field. Standard model tests were also carried out. The test results show that the velocity field of the Mach 4.5 nozzle we developed meets technical requirements. The standard model test data provide data reliable support for the development of aircraft.

摘要

常规跨超声速风洞进行马赫数4.5试验时，常常伴有空气液化现象，造成试验数据可信度低，在高超声速风洞研制马赫数4.5喷管，具有对气流加热的能力，可以提供更加准确的试验数据。目前国内0.5 m量级高超声速风洞还不具备马赫数4.5的试验能力，因此，在高超声速风洞研制马赫数4.5喷管，填补了国内在该区域的空白，具有重要意义。通过无黏流计算方法计算轴对称喷管型面，并采用Sivells-Payne方法进行附面层修正及数值模拟，证明了计算出的型面满足马赫数设计要求。在结构设计上，采取了分三段的设计方法，更加能保证内型面的连续性和光滑性，以得到更加优质的流场结果。流场校测和标模试验结果表明：研制的马赫数4.5喷管速度场满足技术指标要求，标模试验数据规律、量值可信，可以为飞行器研制提供可靠的试验数据，为飞行器研制提供数据支撑。