| 超音速进气道建模方法研究 |
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| 引用本文： | 时瑞军,卢贤锋,樊思齐.超音速进气道建模方法研究[J].航空动力学报,2004,19(4):466-471. |
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| 作者姓名： | 时瑞军 卢贤锋 樊思齐 |
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| 作者单位： | 西北工业大学,动力与能源学院,陕西,西安,710072 |
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| 基金项目： | 西北工业大学青年教师创新基金资助项目(08250207) |
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| 摘 要： | 对某可调混压进气道在不同攻角、不同马赫数、不同斜板角度下进行了大量的数值计算。给出了设计状态下进气道内外流场特征;分析了攻角变化对进气道流场的影响;以数值仿真结果为基础,利用B样条理论建立了反映攻角、马赫数及可调斜板角度变化的超声速进气道数学模型。根据此数学模型,分析了攻角和进口气流马赫数对进气道性能的影响,同时给出了斜板对进气道性能的影响。
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| 关 键 词： | 航空、航天推进系统 进气道 数值仿真 数学模型 B样条 |
| 文章编号： | 1000-8055(2004)04-0466-06 |
| 收稿时间： | 2003/12/30 0:00:00 |
| 修稿时间： | 2003年12月30 |
Investigation of Supersonic Inlet Mathematical Model with Attack Angle |
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| SHI Rui-jun,LU Xian-feng and FAN Si-qi.Investigation of Supersonic Inlet Mathematical Model with Attack Angle[J].Journal of Aerospace Power,2004,19(4):466-471. |
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| Authors: | SHI Rui-jun LU Xian-feng and FAN Si-qi |
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| Institution: | College of Propulsion and Energy,Northwestern Polytechnical University, Xi'an710072,China;College of Propulsion and Energy,Northwestern Polytechnical University, Xi'an710072,China;College of Propulsion and Energy,Northwestern Polytechnical University, Xi'an710072,China |
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| Abstract: | At different attack angles,Mach numbers and ramp angles,the numerical calculations of inner and external flow field are performed for an adjustable mixed compression inlet.The full flow field characteristics of a supersonic inlet are illustrated at design conditions;The influence of attack angle on flow field of the inlet is investigated;B-spline theory is used to model the inlet with attack angle.On basis of the modeling results,the effects of Mach number,attack angle and ramp angle on the inlet performance are analyzed. |
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| Keywords: | aerospace propulsion system mixed compression inlet numerical simulation mathematical model B-spline |
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