不同飞行工况下的某高超飞行器流道特征及气动力特性研究
Study on the flowpath and the aerodynamic characteristic of an hypersonic vehicle at different flight conditions
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摘要: 对一种类似于X-43A飞行器的一体化构形进行了全三维数值仿真模拟,将前体下表面侧沿程静压分布的计算结果与实验结果进行了对比,二者吻合较好,表明数值模拟方法正确,结果可信.在此基础上研究了不同飞行工况下飞行器流道特征及气动力特性的变化.研究结果表明:①研究范围内来流马赫数的变化对全流道的流动结构和全机气动力特性有着一定影响,使得飞行器全机的升阻比略有下降;②随着飞行攻角的改变,全流道的流动结构和升力系数变化显著,而阻力系数的变化并不明显;③侧滑角导致了不对称的流动结构,但在本文的研究范围内其进气道以及全机的气动特性的不利影响并不明显.Abstract: The 3-D flow numerical simulation of a hypersonic vehicle like X43-A was implemented,and the computational static pressure distribution on the undersurface was compared with the experimental data.The comparison shows that the numerical results are consistent well with the measurements.A study was carried out to investigate the aerodynamic characteristics and the full flowpath of the hypersonic vehicle in different flight conditions.Results indicates:(1) With the increase of the free stream Mach number,the full flowpath and the aerodynamic characteristics fluctuate though changes could be found.(2)Despite of the fact that the drag coefficient is not sensitive to the change of the angle of attack,the lift coefficient and the flow structure of the full flowpath is highly affected.(3)The sideslip affects the asymmetric flowpath but with little unfavorable influence on the aerodynamic characteristic.
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Key words:
- hypersonic vehicle /
- flight conditions /
- full flowpath /
- aerodynamic characteristic
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