scramjet

Computation and analysis of aeroheating of scramjet inlet cowl lip

超燃冲压发动机唇口气动热计算研究与分析

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This paper summarized the latestand foreign development status of scramjet engine andthe key technologies.

超燃冲压发动机技术是一项新型的、具有广阔发展前景的推进技术.

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Endothermic hydrocarbon fuels ( EHF) can provide sufficient heat sink for hypersonic scramjet cooling, the total hint sink of EHF come from the physical heating of the fuel and endothermic chemical reaction.

吸热型烃类燃料是一种热安定性好、可以利用其化学热沉的燃料，其热沉能够满足高超音速飞行的需要。

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Computations are done on flow configurations that resemble the reaction zone in the scramjet combustor flows.

本文通过数值模拟得到了超燃冲压发动机燃烧室化学反应流流场的流动结构.

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The scramjet, which is the propulsion of hypersonic vehicle, has become the focus in many military developed countries.

高超音速飞行器的动力装置&超音速燃烧冲压发动机的研究已成为当前各军事强国研究的热点。

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Research on Numerical Simulation of Two-Phase Reacting Flow Field and Combustion Performance of Annular Combustors; Simulation and Experiment of Two-Phase Mixing and Combustion in the Scramjet Combustor

环形燃烧室两相燃烧流场与燃烧性能数值研究超燃冲压发动机燃烧室两相流混合燃烧过程仿真及实验研究

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Computational Study of Contraction Ratio Effects on Scramjet Inlet

不同收缩比超燃冲压发动机进气道的数值研究

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The drag of cavity decreases with increasing fuel equivalence ratio, and could be converted into the thrust, instead of drag, under combustion mode which is close to real statue of scramjet.

在实际超燃冲压发动机工况下，凹腔火焰稳定器的阻力随着当量比的增加而减小，并最终会表现为正推力。

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Effects of vitiated air on the results of ground tests of scramjet combustor

污染空气对超音速燃烧地面试验结果的影响

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Aerodynamic Performance Analysis of Scramjet Isolator under Asymmetric Supersonic Flow

非对称来流条件下超燃冲压发动机隔离段气动特性研究

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A major challenge scramjet engines currently faced is the high aerodynamic heat load. The wall temperature of combustion chamber without cooling can reach 3000K, which exceeds the limit of the general material used.

超燃冲压发动机目前面临的一大难题就是极高的气动力热载荷，燃烧室壁面温度在未经冷却的情况下能达到3000K。这超过了一般结构材料的使用极限。

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The ground test is very important for the research of scramjet.

地面实验是研制超音速燃烧冲压发动机的重要手段。

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This study deals with the effect of vitiated air contamination on combustion and scramjet engine ground tests.

本研究关系到污染对燃烧的影响以及对于超音速燃烧冲压发动机地面试验的影响。

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The main performance parameters of a fixed geometry scramjet are observed, and the effective thrust coefficient, effective specific impulse and effective specific thrust are determined.

探讨了固定几何尺寸（不可调）的超燃冲压发动机有效推力系数、有效比冲和有效单位推力等主要性能参数变化的定量范围。

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Optimized design on a new type thermal structure of scramjet combustor

超燃冲压发动机燃烧室新型热结构的优化设计

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Scramjet nozzle was installed at the exit of the combustor.

尾喷管直接安装在模型发动机的燃烧室出口.

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Elementals Classification and performance of scramjet for cruise missiles are reviewed in this paper.

本文综述了飞航式导弹所用超音速燃烧冲压发动机的基本原理、分类及其特点。

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Influence of Back Pressure on the Inner Flow Field in Scramjet Isolator

反压对超燃冲压发动机隔离段内流场的影响

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Hypersonic propulsion test facility is important for the scramjet ground tests.

摘要高超声速推进风洞是进行超燃冲压发动机模型地面模拟的重要试验设备.

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