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边界层对可调节进气道性能的影响(英文) 被引量:1
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作者 M.A.Goldfeld A.V.Starov k.yu.timofeev 《实验流体力学》 CAS CSCD 北大核心 2013年第1期5-14,共10页
给出了马赫数2~6、单位雷诺数(0.8~6.0)×107/m时下吹式风洞中可调节三维进气道的试验研究结果。研究了前缘前掠和后掠方案以及进气道入口前边界层的影响。测量了内流道内的压力分布、质量流量和总压恢复系数;确定了进气道启动与... 给出了马赫数2~6、单位雷诺数(0.8~6.0)×107/m时下吹式风洞中可调节三维进气道的试验研究结果。研究了前缘前掠和后掠方案以及进气道入口前边界层的影响。测量了内流道内的压力分布、质量流量和总压恢复系数;确定了进气道启动与马赫数和流动工况的关系。研究结果表明:边界层对流场结构和模型进气道的性能有着决定性影响,相对简单的进气道调节方案可以增大其稳定运行范围。 展开更多
关键词 三维高超声速进气道 边界层 下吹式风洞
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Ignition Process Evolution at High Supersonic Velocities in Channel
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作者 M.A.Goldfeldl A.V.Starov +1 位作者 k.yu.timofeev V.A.Vinogradov 《Journal of Thermal Science》 SCIE EI CAS CSCD 2009年第2期166-172,共7页
The results of experimental research of multi-injector combustors in the regime of the attached pipe are presented.As a source of high-enthalpy working gas (air), hot shot wind tunnel IT-302M of ITAM, the Siberian Bra... The results of experimental research of multi-injector combustors in the regime of the attached pipe are presented.As a source of high-enthalpy working gas (air), hot shot wind tunnel IT-302M of ITAM, the Siberian Branch ofthe Russian Academy of Sciences was used. Tests have been carried out at Mach numbers 3,4 and 5, in a range ofchange of total temperature from 2000K up to 3000K and static pressure from 0.08MPa up to 0.23MPa. Injectorsection has been manufactured in two versions with a various relative height of wedge-shaped injectors with parallelfuel injection. Influence of conditions on the entrance of the combustion chamber on ignition and a stablecombustion of hydrogen was investigated. Intensive combustion of hydrogen has been received only at Machnumbers 3 and 4. Advantage of injector section with the greater relative height of injectors is revealed. Themechanism of fuel ignition in the combustion chamber of the given configuration was investigated: two-step ignitionprocess including 'kindling' and intensive combustion over all channel volume. 展开更多
关键词 supersonic combustor IGNITION stable combustion.
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