火星再入飞行器风洞试验与真实飞行之间相关性的探讨

doi:10.13700/j.bh.1001-5965.2018.0434

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摘要由于风洞试验条件限制，难以完全模拟火星再入飞行器真实飞行环境，因此需要建立火星再入飞行器风洞条件与真实飞行之间的关联关系。基于国外文献公开数据，采用数值方法和对比分析方法探讨了类"探路者号"外形的火星再入飞行器的风洞试验与真实飞行之间的外推方法。结果表明，在高焓空气风洞和常规空气风洞试验条件下，可以将模型驻点附近的无量纲压力和压力系数作为相关性参数，将风洞条件与飞行条件相关联起来，但是不能直接利用风洞试验的热流、无量纲热流和Stanton数作为关联参数；在高焓CO₂风洞试验条件下，可以利用模型驻点附近的无量纲压力、压力系数和Stanton数作为外推参数，但是不能直接将风洞试验的热流、无量纲热流作为相关性参数，将风洞条件下的风洞数据通过外推获取飞行条件下飞行器的性能参数。

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	刘方彬
	袁军娅

关键词 ：火星, 高超声速, 风洞, 再入, 相关性, 气动力, 气动热

Abstract：Due to the limitations of wind tunnel test conditions, the real flight environment of Mars reentry aircraft is difficult to fully be simulated, so it is necessary to establish the relationship of Mars reentry vehicle between windtunnel conditions and real flight. In this investigation, based on the published data of the literatures, the numerical method is used to study the extrapolation methods between the wind tunnel test and the real flight of Mars re-entry vehicle with the shape of the Pathfinder. The results show that under the conditions of high enthalpy air wind tunnel and conventional air wind tunnel test, the dimensionless pressure and pressure coefficient of near the stagnation point of the windtunel model can be used as a correlation parameters between the wind tunnel that and the flying conditions. However, the heat flow, the dimensionless heat flow and Stanton number of wind tunnel test cannot be directly used as correlation parameters under the conditions of high enthalpy air wind tunnel test and conventional air wind tunnel test. Under the high enthalpy CO₂ wind tunnel test conditions, the pressure coefficient, dimensionless pressure and Stanton number near the windtunnel model's stagnation point can be used as extrapolation parameters, but not the heat flow and dimensionless heat flow of the wind tunnel test are directly used as correlation parameters to obtain the performance parameters of the aircraft under flight conditions.

Key words： Mars hypersonic wind tunnel reentry correlation aerodynamic force aerothermodynamics

收稿日期: 2018-07-18

PACS:

V476.4

通讯作者: 袁军娅 E-mail: yuanjy@buaa.edu.cn

作者简介: 刘方彬,男,硕士。主要研究方向:高超速飞行器化学反应;袁军娅,女,硕士生导师,高级工程师。主要研究方向:高超声速飞行器气动热环境与热防护。

引用本文:

刘方彬, 袁军娅. 火星再入飞行器风洞试验与真实飞行之间相关性的探讨[J]. 北京航空航天大学学报, 2019, 45(4): 787-795.
LIU Fangbin, YUAN Junya. Discussion on correlation between wind tunnel test and flight of Mars reentry vehicle. JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2019, 45(4): 787-795.

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http://bhxb.buaa.edu.cn/CN/10.13700/j.bh.1001-5965.2018.0434 或 http://bhxb.buaa.edu.cn/CN/Y2019/V45/I4/787

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