高超声速内外流动激波/边界层相互作用的实验与数值研究
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摘要
在吸气式高超声速飞行器内、外流场中,激波/边界层相互作用是一类不可忽视的重要流动现象。它会导致流场中空间波系的剧烈改变和壁面流动分离。同时带来飞行器气动力、气动热负荷的分布不均匀与非定常振荡。严重时会引起进气道的不起动,影响发动机的正常工作。分析激波/边界层相互作用的产生机理、演化规律与影响,并利用流动控制手段加以削弱和消除壁面流动分离,改善飞行器内外流场的流动品质,具有十分重要的工程意义和实际价值。
本文通过实验研究和数值模拟相结合的方法,考察了多种基本构型以及典型高超声速进气道内部的激波/边界层相互作用现象。研究中考察了流场的空间波系结构、边界层内部流动特征以及壁面的压力、热流密度分布等参量。讨论了流动现象与构型参数之间的关系及演化规律。分析了激波/边界层相互作用现象对进气道工作状态的影响。针对不同构型条件下的激波/边界层相互作用,讨论分析了流动控制技术对于壁面流动分离的控制效果以及其他流动参数的改善状况。最后对激波/激波干扰的相关实验做了简要的介绍。
本文取得的主要结果与进展如下：
1、对二维基本构型的实验和数值研究得到了激波/边界层相互作用诱发壁面分离随激波强度变化的变化趋势,数值模拟和实验研究得到了较好的符合。针对二维斜激波/平板边界层相互作用,考察了吹除控制手段对壁面流动分离的控制效果和若干影响因素。得到了吹除总温、总压与分离区尺度以及壁面流动参量分布的关系。考察了不同吹除工质及多种工质的混合物对吹除控制效果的影响,得到了若干定性的结论。
2、在实验中考察了两级压缩的二维顶压式进气道内部激波/边界层相互作用的流场特征及对进气道工作状态的影响并考察了涡发生器与粗糙壁面对压缩面交界处流动分离的控制效果。利用数值模拟手段考察了两种来流条件下唇口位置的流动分离特征及抽吸手段的对壁面分离的控制效果及进气道内部流动参数的改善状况。
3、发展了新的以近壁面流动特征为关注对象的可应用于激波风洞等高速空气动力学试验设备中的丝线方法,并将其应用于三维激波/边界层相互作用的壁面流动特征观测。实验结果证明了该方法的有效性以及简便性、实时性等优点。针对平板-鳍板构型的三维激波/边界层相互作用的空间波系特征与壁面流动参数分布也通过数值手段得到了考察和分析。
4、利用多种流动显示方法观测了三组三面压缩进气道内部的激波/边界层相互作用现象,讨论分析了进气道内部的空间波系和壁面流动的特征。实验中也考察了抽吸控制方法对进气道内部壁面流动分离的控制效果。
5、最后简单讨论了实验中得到的激波/激波干扰的相关结果,对激波/激波干扰现象建立基本的了解。
Shock wave/boundary layer interaction(SWBLI) is an important phenomenon in hypersonic air-breathing vehicles, which may cause not only harmful flow of no uniformity, total pressure loss, inlet unstart etc., but also bring about severe heat loads which may be far beyond the capability of predictions.
In present thesis, some basic physical configurations and two kinds of hypersonic inlet are tested to investigate the SWBLI behaviors with experimental and numerical methods. Structure of shock waves and flow phenomenon close to the surface of the model are observed and pressure, shear stress and heat flux over the surface are analyzed. Furthermore, effect of flow control technology to weaken viscous separation is also evaluated. Some experimental results of shock wave/shock wave interaction are also analyzed.
The main results of present work are:
1, Results of two dimensional basic figures show the behaviors of SWBLI would change with grown strength of the shock wave. For the case of oblique shock wave impinges on the plate, blowing method was tested to weaken the separation caused by the SWBLI. Groups of data from numerical simulation were analyzed to show how flow phenomenon change with different total pressure and total temperature of the blowing jet. Several kinds of gases and mixtures as blowing jet were discussed and analyzed.
2, Experiments were carried out to investigate the SWBLI phenomenon in a two-dimensional hypersonic inlet with two wedge ramps, especially for the condition when the inlet is close to unstarting flow. Roughness surface and vortex generators were used to impair the separation at the corner of two ramps. Separations arising at downstream of the cowl at different conditions of free stream were analyzed and discussed. Effect of bleeding to weaken the viscous separation was also evaluated by numerical simulation.
3, A new kind of tuft method, which is conventionally used in low speed wind tunnels, was developed for using in the shock tunnel to observe details of flow field close to the surface. It was proved that the tuft method can visualize the near-wall dynamic behaviors effectively. SWBLI phenomenons over three-dimensional configurations were investigated by the tuft method, oil dot visualization and numerical simulation. Flow structures and some related parameter variations on the surface were revealed and analyzed.
4, Several kinds of flow visualization technology were employed to observe flow field in the three-dimensional hypersonic inlet, which were also analyzed with supplement from the results of simulation. Bleeding was also examined to evaluate the control effectiveness of the separation.
5, Some experimental results of shock wave/shock wave interaction were demonstrated, which is helpful for the better understanding of this flow phenomena.
本文通过实验研究和数值模拟相结合的方法,考察了多种基本构型以及典型高超声速进气道内部的激波/边界层相互作用现象。研究中考察了流场的空间波系结构、边界层内部流动特征以及壁面的压力、热流密度分布等参量。讨论了流动现象与构型参数之间的关系及演化规律。分析了激波/边界层相互作用现象对进气道工作状态的影响。针对不同构型条件下的激波/边界层相互作用,讨论分析了流动控制技术对于壁面流动分离的控制效果以及其他流动参数的改善状况。最后对激波/激波干扰的相关实验做了简要的介绍。
本文取得的主要结果与进展如下：
1、对二维基本构型的实验和数值研究得到了激波/边界层相互作用诱发壁面分离随激波强度变化的变化趋势,数值模拟和实验研究得到了较好的符合。针对二维斜激波/平板边界层相互作用,考察了吹除控制手段对壁面流动分离的控制效果和若干影响因素。得到了吹除总温、总压与分离区尺度以及壁面流动参量分布的关系。考察了不同吹除工质及多种工质的混合物对吹除控制效果的影响,得到了若干定性的结论。
2、在实验中考察了两级压缩的二维顶压式进气道内部激波/边界层相互作用的流场特征及对进气道工作状态的影响并考察了涡发生器与粗糙壁面对压缩面交界处流动分离的控制效果。利用数值模拟手段考察了两种来流条件下唇口位置的流动分离特征及抽吸手段的对壁面分离的控制效果及进气道内部流动参数的改善状况。
3、发展了新的以近壁面流动特征为关注对象的可应用于激波风洞等高速空气动力学试验设备中的丝线方法,并将其应用于三维激波/边界层相互作用的壁面流动特征观测。实验结果证明了该方法的有效性以及简便性、实时性等优点。针对平板-鳍板构型的三维激波/边界层相互作用的空间波系特征与壁面流动参数分布也通过数值手段得到了考察和分析。
4、利用多种流动显示方法观测了三组三面压缩进气道内部的激波/边界层相互作用现象,讨论分析了进气道内部的空间波系和壁面流动的特征。实验中也考察了抽吸控制方法对进气道内部壁面流动分离的控制效果。
5、最后简单讨论了实验中得到的激波/激波干扰的相关结果,对激波/激波干扰现象建立基本的了解。
Shock wave/boundary layer interaction(SWBLI) is an important phenomenon in hypersonic air-breathing vehicles, which may cause not only harmful flow of no uniformity, total pressure loss, inlet unstart etc., but also bring about severe heat loads which may be far beyond the capability of predictions.
In present thesis, some basic physical configurations and two kinds of hypersonic inlet are tested to investigate the SWBLI behaviors with experimental and numerical methods. Structure of shock waves and flow phenomenon close to the surface of the model are observed and pressure, shear stress and heat flux over the surface are analyzed. Furthermore, effect of flow control technology to weaken viscous separation is also evaluated. Some experimental results of shock wave/shock wave interaction are also analyzed.
The main results of present work are:
1, Results of two dimensional basic figures show the behaviors of SWBLI would change with grown strength of the shock wave. For the case of oblique shock wave impinges on the plate, blowing method was tested to weaken the separation caused by the SWBLI. Groups of data from numerical simulation were analyzed to show how flow phenomenon change with different total pressure and total temperature of the blowing jet. Several kinds of gases and mixtures as blowing jet were discussed and analyzed.
2, Experiments were carried out to investigate the SWBLI phenomenon in a two-dimensional hypersonic inlet with two wedge ramps, especially for the condition when the inlet is close to unstarting flow. Roughness surface and vortex generators were used to impair the separation at the corner of two ramps. Separations arising at downstream of the cowl at different conditions of free stream were analyzed and discussed. Effect of bleeding to weaken the viscous separation was also evaluated by numerical simulation.
3, A new kind of tuft method, which is conventionally used in low speed wind tunnels, was developed for using in the shock tunnel to observe details of flow field close to the surface. It was proved that the tuft method can visualize the near-wall dynamic behaviors effectively. SWBLI phenomenons over three-dimensional configurations were investigated by the tuft method, oil dot visualization and numerical simulation. Flow structures and some related parameter variations on the surface were revealed and analyzed.
4, Several kinds of flow visualization technology were employed to observe flow field in the three-dimensional hypersonic inlet, which were also analyzed with supplement from the results of simulation. Bleeding was also examined to evaluate the control effectiveness of the separation.
5, Some experimental results of shock wave/shock wave interaction were demonstrated, which is helpful for the better understanding of this flow phenomena.
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