T型尾翼风洞颤振实验保护装置绕流特性分析 |
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引用本文: | 史爱明,戎亚楠,杨永年.T型尾翼风洞颤振实验保护装置绕流特性分析[J].气动实验与测量控制,2013(4):57-61,77. |
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作者姓名: | 史爱明 戎亚楠 杨永年 |
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作者单位: | 西北工业大学翼型叶栅空气动力学国防科技重点实验室,西安710072 |
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基金项目: | 国家自然科学基金(10602046); 西北工业大学基础研究基金(JC201128); “翱翔”之星人才计划资助 |
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摘 要: | 采用SST两方程湍流模型,通过求解非定常Navier-Stokes(N-S)方程,对T型尾翼风洞实验流场进行了模拟,分析了保护装置对T型尾翼风洞实验流场的影响,研究了保护装置几何外形和保护装置基座后移距离对流场影响。通过对平尾气动力的分析以及对非定常流场的对比,可以得出:采用NACA系列翼型对基座进行气动整流后,基座两侧局部超声速区显著减小,局部激波减弱甚至消失,流场品质得到改善。且采用NACA0010翼型对基座修形后的结果最理想。随着保护装置基座后移距离的增加,平尾气动力均方根值和波动值先是急剧减小,达到0.85倍平均气动弦长后开始有所增大,在2.45~4.05倍平均气动弦长范围基本不再变化,稳定到单独T型尾翼模型相应系数1倍左右。此结论对T型尾翼风洞颤振实验保护装置设计具有一定的指导意义。
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关 键 词: | T型尾翼 SST模型 Navier-Stokes方程 颤振实验保护装置 |
Improvement of shielding-test-facilities for the T-tails in flutter wind-tunnel experiments |
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Authors: | SHI Ai-ming RONG Ya-nan YANG Yong-nian |
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Institution: | (National Key Laboratory of Aerodynamic Design and Research,Northwestern Polytechnical University,Xi'an 710072,China) |
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Abstract: | The unsteady flow around the T-tails flutter model with a set of shielding-test-facilities in wind tunnel experiments were solved by applying Reynolds-Averaged Navier-Stokes(RANS)equations with SST turbulence model.Two key points were studied,one was the section shapes along airflow for shielding-test-facilities;the other was the distance between the shielding-test-facilities and the T-tails wind tunnel model.The aerodynamic bending-moments and normal-forces indexes versus the calculating time-step were presented.When a series of NACA airfoils(NACA0010-airfoil,NACA0015-airfoil,NACA0021-airfoil)were selected to enwrap the base of shielding-test-facilities,the characteristics of the flow around the T-tails flutter model with the modified shielding-test-facilities were running to quasi-steady.The strength of shock wave decreasing and the vibration of shock wave fading were deduced to the whys.The improvement of NACA0010-airfoil was much better than the others.The Root-Mean-Square(RMS)and the amplitude in the first period for the aerodynamic coefficients(bending-moments and normalforces)versus the distance between the shielding-test-facilities and the T-tails flutter model were figured out.When the distance between the shielding-test-facilities and the T-tails wind tunnel model was increased from 2.45cto 4.05c(c was the mean-aerodynamic chord of vertical-fin),the aerodynamic coefficients were almost constant. |
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Keywords: | T-tail SST model Navier-Stokes equation flutter shielding-test-facility |
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