查询词典 scramjet

Judgment criterion of scramjet inlet unstart control and position choosing strategy between P1 and P2 are provided.

给出了冲压发动机进气道不起动控制的判断准则和P1、P2位置选择的策略。

In this paper, experimental study (Ma=2.0 of cold flow) on a scramjet combustor model without combustion was carried on direct-connected facility. The effects of inflow parameter, length of isolator and back pressure on combustor and isolator flow field were analyzed and compared. The flow field of combustor was simulated with CFD software and the experimental results were compared.

文中在超燃冲压发动机燃烧室直连式实验设备上，对超音速燃烧室模型进行( Ma ＝2.0)冷流实验研究，比较了不同的来流条件、不同的隔离段长高比和不同的燃烧室出口反压对燃烧室内部流场以及燃烧室隔离段的抗扰动能力的影响，并利用数值模拟的方法对燃烧室内部流场进行了模拟。

The preliminary study on the influential factors of scramjet combustor wall pressure was carried out on the direct-connected test facilities under the simulated condition of 25km, 6Ma.

采用试验研究的方法，在模拟飞行高度25km、来流马赫数6的情况下，在直连式试验台上对超燃冲压发动机燃烧室压力影响因素进行了初步研究。

Scramjet ; direct-connected facility ; experimental research ; blockage ratio ; numerical simulation

超燃冲压发动机；直连式设备；实验研究；堵塞比；数值模拟

In the paper, the resistance heated and continuous facility is adopted to finish scramjet combustor experiment research on hydrogen-fueled and ethylene-fueled ignition and combustion at different equivalence ratio. The continuous clean airflow of flow ratio 0.73kg/s, total temperature Tt=1000K, Mach number M=2.0, total pressure Pt=0.8MPa is available to the inlet of direct-connected experimental model.

本文采用电阻加热的连续式实验设备，在燃烧室进口气流为高温纯净空气、Ma数M=2、总温Tt=1000K，总压Pt=0.8MPa条件下，进行了不同当量油气比的氢和乙烯燃料的超音速燃烧室直连式实验。

Experimental investigations on the combustion process of a liquid hydrocarbon fuel ed scramjet, ignited by hydrogen pilot flame, and with four different inlets, were conducted in free-jet tests, which simulated the fly conditions of Ma=6 and H=25km.

在模拟飞行马赫数Ma=6，高度25km条件的液体碳氢燃料超燃冲压发动机自由射流试验中，对比研究了4种不同进气道，不同燃烧室入口条件下模型发动机的点火与燃烧性能。

Experimental investigations on the combustion process of a liquid hydrocarbon fueled scramjet, ignited by hydrogen pilot flame, and with four different inlets, were conducted in free-jet tests, which simulated the fly conditions of Ma=6 and H=25km.

在模拟飞行马赫数Ma=6，高度25km条件的液体碳氢燃料超燃冲压发动机自由射流试验中，对比研究了4种不同进气道，不同燃烧室入口条件下模型发动机的点火与燃烧性能。

The supersonic interacting flowfield induced by gaseous secondary flow injected into supersonic flow is typical and encountered in many fields, such as thrust vector control, gas-turbine cooling, and fuel-air premixing in scramjet engines, et al.

二次射流与超音速来流的干扰流场主要应用在推力矢量控制、飞行器气动控制、超音速燃烧和气膜冷却等方面。因为其复杂性和应用的广泛性，二次射流干扰流场多年以来一直是流体力学界的重要研究课题。

Regenerative cooling technology is one of the key technologies to thermally protect scramjet chamber.

摘要再生冷却技术是超燃冲压发动机燃烧室热防护的关键技术。

Thermal cracking of China No.3 aviation kerosene was studied experimentally under supercritical conditions relevant to regenerative cooling system for Mach-6 scramjet applications.

本文介绍了大庆3号煤油在超临界条件下热裂解特性的实验研究。

The split between the two groups can hardly be papered over.

这两个团体间的分歧难以掩饰。

This approach not only encourages a greater number of responses, but minimizes the likelihood of stale groupthink.

这种做法不仅鼓励了更多的反应，而且减少跟风的可能性。