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| 1 | Numerical investigation of unsteady vortex breakdown past 80°/65° double-delta wing显示文摘An improved delayed detached eddy simulation(IDDES) method based on the k-x-SST(shear stress transport) turbulence model was applied to predict the unsteady vortex breakdown past an 80 /65 double-delta wing(DDW), where the angles of attack(AOAs) range from 30 to 40. Firstly, the IDDES model and the relative numerical methods were validated by simulating the massively separated flow around an NACA0021 straight wing at the AOA of 60.The fluctuation properties of the lift and pressure coefficients were analyzed and compared with the available measurements. For the DDW case, the computations were compared with such measurements as the mean lift, drag, pitching moment, pressure coefficients and breakdown locations.Furthermore, the unsteady properties were investigated in detail, such as the frequencies of force and moments, pressure fluctuation on the upper surface, typical vortex breakdown patterns at three moments, and the distributions of kinetic turbulence energy at a stream wise section.Two dominated modes are observed, in which their Strouhal numbers are 1.0 at the AOAs of30, 32 and 34 and 0.7 at the AOAs of 36, 38 and 40. The breakdown vortex always moves upstream and downstream and its types change alternatively. Furthermore, the vortex can be identified as breakdown or not through the mean pressure, root mean square of pressure, or even through correlation analysis. | Liu Jian Sun Haisheng Liu Zhitao Xiao Zhixiang | 2014 | Chinese Journal of Aeronautics2014，27，3： | 12 |
| 2 | 宽速域RANS-LES混合方法的发展及应用显示文摘传统的雷诺平均方法(RANS)已经不能满足大范围分离、激波振荡、压力脉动、动载荷等极端工况下的流动预测需求;大涡模拟(LES)、直接数值模拟(DNS)等方法资源耗费多、效率低,离工程湍流问题仍较为遥远。RANSLES混合方法结合了RANS高效率和LES高精度的特点,近期有望大规模应用到工程湍流问题中。首先对现有的RANS-LES混合方法进行了归类,对各自的构造思想、特点进行了分析。然后报告了脱体涡模拟(DES)类方法的发展历程和现状,讨论了使用DES类方法计算分离流动时,对流项离散格式对分离特性、小尺度结构及频谱特性等的影响,并构造了自适应耗散函数。最后介绍了近年来国内外RANS-LES混合方法在宽马赫数范围(马赫数从0.1到20)内的机理研究和工程应用。现有的以DES类方法为代表的RANS-LES混合方法能够较为精细地模拟非定常大分离流动中的复杂现象,但在计算效率等方面还有较大的改进空间;植入式DES方法在模拟全机带部件流动上具有较高的效率和模拟精度,是重要的发展方向。RANS-LES混合方法在动态失速、燃烧、气动弹性、气动噪声、气动光学等与非定常流动密切相关的方面也有广阔的应用前景。 | 肖志祥 罗堃宇 刘健 | 2017 | 空气动力学学报2017，35，3： | 12 |
| 3 | 多段翼型缝翼前缘结冰大迎角分离流动数值模拟显示文摘应用基于SST(Shear-Stress-Transport)湍流模型的IDDES(Improved Delayed Detached Eddy Simulation)方法,对大迎角状态下多段翼型缝翼前缘典型角状冰引起的复杂分离流动进行了数值模拟研究。采用后台阶流动标准算例和干净无冰多段翼型分离流动算例对数值方法的可靠性和适用性进行了验证。缝翼结冰状态下的数值模拟结果表明:来流迎角较大时,前缘角状冰将会导致结构相对稳定的流动分离泡产生,分离泡的非定常尾迹会对主翼前缘附近流场产生较为强烈的干扰,抑制了缝道流动的加速效应,使得缝翼增升效率降低。在失速点附近,由于分离泡回流强度随来流迎角而增长,同时脱落旋涡的输运方向逐渐向远离壁面方向偏移,使得尾迹影响区域范围和强度均有所增加。 | 张恒 李杰 龚志斌 | 2017 | 航空学报2017，38，2： | 11 |
| 4 | Direct numerical simulation of hypersonic transition induced by an isolated cylindrical roughness element显示文摘Hypersonic boundary layer transition induced by an isolated cylindrical roughness element is investigated using direct numerical simulation method based on a finite volume formulation.To simulate the transition procedure by resolving the generation and evolvement of small-scale coherent structures,and capture the shock wave at the same time,high-order minimum dispersion and controllable dissipation scheme is validated and then applied.The results are compared with the available measurements in the quiet wind tunnel,such as the dominated frequency and root mean square of pressure.The computational dominated frequency of 19.23 k Hz is very close to the experimental one,21 k Hz.Also,the disturbances of the roughness are mostly generated by the'jet'just before the roughness,and then they travel and develop downstream with the shear layer and vortex shedding.The transition is mainly dominated by the instabilities of both the horseshoe vortex and the shear layer. | DUAN Zhi Wei XIAO Zhi Xiang FU Song | 2014 | Science China(Physics,Mechanics & Astronomy)2014，57，12： | 11 |
| 5 | 机翼跨声速抖振研究进展显示文摘跨声速飞行中,激波附面层干扰会引起激波周期性自激振荡,这种现象称之为跨声速抖振。跨声速抖振引起的脉动载荷有可能造成结构疲劳甚至引发飞行事故,该问题一直是航空领域的研究难点。本文从风洞试验和数值模拟两个方面总结了跨声速抖振研究的主要方法,重点综述了近几年在跨声速抖振机理研究方面以及结构运动对抖振响应特性的影响方面取得的新进展,简要总结了跨声速抖振的被动控制及主动控制方法。在此基础上,提出了跨声速抖振后续研究的重点方向:抖振机理的进一步探究,结构弹性特征对抖振特性的影响以及闭环主动控制等。 | 张伟伟 高传强 叶正寅 | 2015 | 航空学报2015，36，4： | 10 |
| 6 | 基于iDDES的双三角翼大迎角非定常涡破裂特征分析显示文摘采用基于两方程k-ω-SST模型的i DDES方法对80°/65?双三角翼涡破裂流动进行了数值模拟,获得了迎角?=30??40?范围内,涡破裂在双三角翼主翼面上方发生时的气动力、表面压力、空间涡结构、湍动能等流动信息,在与风洞实验充分比对的基础上,详细分析了涡破裂发生时的涡破裂形态,表面压力均方根值分布,非定常气动力、表面压力脉动等流动特征,对涡破裂与气动力频谱、表面压力/压力脉动、空间速度、湍动能分布之间的相互关系进行了阐述,并分析了以这些流动信息为判据得到的涡破裂位置之间的相关性。 | 刘健 蒋永 吴金华 | 2016 | 工程力学2016，33，4： | 7 |
| 7 | A Karman-Vortex Generator for passive separation control in a conical diffuser显示文摘Flow separation in a conical diffuser with large divergence angle(29.14°) and large area ratio(3.533) is eliminated by a novel passive flow control device called Karman-Vortex Generator(KVG).The effect of the KVG is verified and investigated by the URANS,DES and DDES methods based on the SST model.CFD results show that the performance coefficient of the diffuser can be doubled by the KVG,and the total pressure recovery coefficient can be improved by about 1.2%.DES and DDES results show that the KVG can introduce a Karman-vortex street frequency in the diffuser.This frequency decays rapidly,and could not be detected in the ending plane of the expansion section.Different KVG configurations with different locations and dimensions are numerically simulated and compared.Some suggestions are provided. | ZHANG YuFei CHEN HaiXin FU Song | 2012 | Science China(Physics,Mechanics & Astronomy)2012，55，5： | 7 |
| 8 | 基于RANS/LES方法的超声速底部流场数值模拟显示文摘分别采用基于两方程k-ω剪切应力输运(SST)湍流模型的延迟DES(DDES)、更改的DDES(MDDES)和改进的DDES(IDDES)方法,并引入可压缩修正,结合三阶MUSCL-Roe和五阶WENO-Roe两种空间离散格式,针对超声速底部的复杂流动现象,开展了数值模拟研究。计算结果表明本文方法能够捕捉到超声速底部流动中丰富的湍流结构,通过分析计算结果对超声速底部的流动机理有了进一步的认识,为下一步的超声速底部流动减阻改进和雷诺平均NavierStokes/大涡模拟(RANS/LES)方法在非定常高可压缩性流动中的应用提供了参考。通过对比分析不同空间离散格式的计算结果研究了数值耗散对计算的影响,五阶WENO-Roe格式的计算结果与实验结果吻合良好;对不同RANS/LES混合方法的计算结果进行了对比分析,结果表明IDDES方法在近壁区的表现优于DDES和MDDES方法。 | 张露 李杰 | 2017 | 航空学报2017，38，1： | 5 |
| 9 | Detached-eddy simulations and analyses on new vortical flows over a 76/40° double delta wing显示文摘Numerical simulations were performed on the massively separated flows of a 76/40° double delta wing using detached-eddy simulation(DES).A new type of cross-flow vortex is suggested.A vortex was initially generated near the junction of the strake and wing,which then moved towards the wing tip at certain wavelength and speed.Analyses were made in detail on the mechanism of the generation of the cross-flow vortex,that is,the inviscid cross-flow instability which differs from that of the swept blunt wing.Cross-section topology of the cross-flow vortex is also investigated,and the wavelength of the vortex array and the characteristic frequency are given.The analyses showed that the cross-flow vortices have an influence on the pressure distribution,which can cause a 10%-20% deviation from the averaged distribution. | LI Qin SUN Dong ZHANG HanXin | 2013 | Science China(Physics,Mechanics & Astronomy)2013，56，6： | 5 |
| 10 | NACA0012翼型抖振现象实验研究显示文摘通过在风洞侧壁安装动态压力传感器测量侧壁脉动压力的方法针对NACA0012翼型开展了零攻角状态下跨声速抖振特性的实验研究,并测量了翼型沿弦向与展向的压力分布。从时域和频域两个方面分析了脉动压力结果,得到了NACA0012翼型的跨声速抖振起始马赫数和抖振频率等抖振特性。研究结果表明:风洞二维性较好,侧壁区域的压力情况能够反映核心流压力变化情况;抖振发生在实验马赫数Maexp=0.88~0.89范围内;随着马赫数的增大,抖振频率有所增加。 | 任旭东 赵子杰 高超 李峰 | 2015 | 工程力学2015，32，5： | 5 |
| 11 | 基于谐振舵面的跨声速抖振抑制探究显示文摘跨声速抖振引起的非定常脉动载荷会造成飞行器结构疲劳甚至引发飞行事故,所以跨声速抖振的控制研究逐渐成为航空领域的热点。采用基于Spalart-Allmaras(S-A)湍流模型的非定常雷诺平均方程开展了基于谐振舵面的跨声速抖振抑制研究。首先验证静止NACA0012翼型的抖振边界和频率特性,然后分别从舵偏平衡位置、舵偏幅值、频率以及相角等角度研究了谐振舵面的控制效果。舵偏平衡位置等效于减小了翼型的有效迎角;幅值和频率对抖振抑制效果影响较大,当舵面振荡频率与抖振频率接近时发生共振现象;相角对控制效果有一定影响,在270°相角附近,升力系数幅值减小了60%。在合适的舵偏幅值、频率以及相角组合下,谐振舵面有可能成为跨声速抖振的有效开环控制策略。 | 高传强 张伟伟 叶正寅 | 2015 | 航空学报2015，36，10： | 4 |
| 12 | Numerical study on the correlation of transonic single-degree-of-freedom flutter and buffet显示文摘Transonic single-degree-of-freedom(SDOF) flutter and transonic buffet are the typical and complex aeroelastic phenomena in the transonic flow. In this study, transonic aeroelastic issues of an elastic airfoil are investigated using Unsteady Reynolds-Averaged Navier-Stokes(URANS) equations. The airfoil is free to vibrate in SDOF of pitching. It is found that, the coupling system may be unstable and SDOF self-excited pitching oscillations occur in pre-buffet flow condition, where the free-stream angle of attack(AOA) is lower than the buffet onset of a stationary airfoil. In the theory of classical aeroelasticity, this unstable phenomenon is defined as flutter. However, this transonic SDOF flutter is closely related to transonic buffet(unstable aerodynamic models) due to the following reasons. Firstly, the SDOF flutter occurs only when the free-stream AOA of the spring suspended airfoil is slightly lower than that of buffet onset, and the ratio of the structural characteristic frequency to the buffet frequency is within a limited range. Secondly, the response characteristics show a high correlation between the SDOF flutter and buffet. A similar 'lock-in' phenomenon exists, when the coupling frequency follows the structural characteristic frequency. Finally, there is no sudden change of the response characteristics in the vicinity of buffet onset, that is, the curve of response amplitude with the free-stream AOA is nearly smooth. Therefore, transonic SDOF flutter is often interwoven with transonic buffet and shows some complex characteristics of response, which is different from the traditional flutter. | GAO ChuanQiang ZHANG WeiWei LIU YiLang YE ZhengYin JIANG YueWen | 2015 | Science China(Physics,Mechanics & Astronomy)2015，58，8： | 4 |
| 13 | 使用IDDES方法预测飞行速度对喷流噪声的影响显示文摘使用变网格尺度定义的IDDES方法,预测了飞行速度对喷流噪声的影响。分析具有试验数据的喷流状态(Ma=0.9,基于喷管直径D的Re_D=1.1×10~6),通过与试验结果的对比,验证方法的正确性,并做了网格敏感性分析,对比了不同FW-H方程积分面对结果的影响。增加自由来流马赫数会增加喷流势流核的长度,降低势流核结束位置的湍动能,降低远场噪声辐射。对远场噪声的影响规律与试验测量值相符,说明此方法适用于存在飞行速度的喷流噪声问题的预测。 | 朱文庆 肖志祥 符松 | 2018 | 空气动力学学报2018，36，3： | 4 |
| 14 | Calibration of a new very large eddy simulation(VLES)methodology for turbulent flow simulation显示文摘Following the idea of Speziale's Very Large Eddy Simulation(VLES) method,a new unified hybrid simulation approach was proposed which can change seamlessly from RANS(Reynolds-Averaged Navier-Stokes) to LES(Large Eddy Simulation) method depending on the numerical resolution.The model constants were calibrated in accordance with other hybrid methods.Besides being able to approach the two limits of RANS and LES,the new model also provides a proper VLES mode between the two limits,and thus can be used for a wide range of mesh resolutions.Also RANS simulation can be recovered near the wall which is similar to the Detached Eddy Simulation(DES) concept.This new methodology was implemented into Wilcox's k-ω model and applications were conducted for fully developed turbulent channel flow at Reτ = 395 and turbulent flow past a square cylinder at Re = 22000.Results were compared with LES predictions and other studies.The new method is found to be quite efficient in resolving large flow structures,and can predict satisfactory results on relative coarse mesh. | HAN XingSi YE TaoHong CHEN YiLiang | 2012 | Science China(Physics,Mechanics & Astronomy)2012，55，10： | 2 |
| 15 | 战斗机垂尾脉动压力数值模拟显示文摘在亚跨超计算流体力学(CFD)软件平台(TRIP)上开发了基于RANS/LES混合思路的IDDES流动模拟技术,并通过NACA0021翼型60°大迎角分离流动与串列圆柱绕流模拟对RANS/LES混合方法的精确度进行了验证,针对某战斗机外形的垂尾脉动压力开展了数值模拟研究。战斗机来流马赫数为0.1,基于全机长度的雷诺数为2×106,模型迎角为20°、30°和40°。分别通过脉动压力系数、脉动压力功率谱密度、空间流动结构以及侧向力响应曲线等对战斗机的垂尾脉动压力进行了分析。脉动压力模拟结果表明:当垂尾完全沉浸在边条翼脱体涡破碎后的宽频湍流脉动气流中时,垂尾翼梢位置的脉动压力会发生明显的增大。 | 孟德虹 孙岩 王运涛 李伟 | 2016 | 航空学报2016，37，8： | 2 |
| 16 | 跨声速抖振锁频状态下的自适应控制方法显示文摘跨声速流固耦合控制是气动弹性研究领域备受关注的研究分支,然而,由于锁频现象耦合模式的复杂性,针对该条件下的行之有效的流固耦合控制方法目前还不多见。考虑到抖振中锁频状态本质上为流动模态与结构模态的失稳,难以通过单一的控制律进行抑制。因此,提出了一种多反馈回路的无模型自适应控制方法,通过引入结构位移与气动力响应数据,结合无模型自适应控制方法,对马赫数0.7、迎角5.5°这一典型抖振状态下的流固耦合模型进行仿真状态下的闭环控制研究。结果表明通过引入结构与气动输出作为控制参数,可以对锁频失稳模式进行有效抑制,通过控制模式的切换,可以对锁频状态下的翼型流动、结构失稳进行控制。 | 王旭 任凯 高传强 孔轶男 张伟伟 | 2020 | 空气动力学学报2020，38，5： | 2 |
| 17 | 激波控制鼓包对跨声速抖振影响的数值研究显示文摘在跨声速飞行时,激波控制鼓包不仅能够减弱机翼上表面的激波强度从而降低波阻,对跨声速抖振也有一定的改善作用。通过URANS方法数值模拟来探究二维激波控制鼓包对OAT15A超临界翼型跨声速抖振性能的影响规律,并研究以巡航设计点减阻与抖振状态减振2种目标设计的鼓包的区别。以巡航设计点减阻优化设计出的鼓包,在抖振条件下,能够推迟了翼型上表面的压力恢复,减弱了激波与边界层的相互干扰作用,达到减弱抖振幅度的效果,然而不能对抖振实现完全抑制。通过改变鼓包相对位置、高度和长度计算得到鼓包参数对抖振的影响规律,分析典型流场得到鼓包抑制抖振现象的工作机理是:鼓包减弱了激波强度的同时,阻碍了鼓包尾部边界层向上游移动与激波相互干扰,从而稳定了激波抖振现象。另外,基于巡航设计点减阻设计的2个鼓包相对参考位置距离分别为0.04c和0.10c(c为翼型弦长),与同等高度鼓包在抖振状态完全抑制抖振且不降低升力的位置范围的[-0.01,0.02]c和[0.01,0.08]c不同,二者位置最小相差0.02c,而鼓包这段距离差异对巡航特性和抖振性能都有着重要影响作用。总而言之,以巡航设计点减阻与抖振状态减振2种目标设计得到鼓包位置上存在偏差,工程设计中应当综合考虑在二者中做出权衡取舍,才能设计出综合性能更好的激波控制鼓包来提升翼型的跨声速性能。 | 章胜华 邓枫 覃宁 刘学强 | 2022 | 航空学报2022，43，11： | 1 |
| 18 | 翼型激波抖振的无模型自适应控制显示文摘由于受到流动环境中的不确定因素影响,针对流动系统设计的闭环控制律需要考虑这些不确定因素,自动适应随机扰动和突发扰动。基于流动模型所设计的闭环最优控制,虽然可以以较小的控制量获得满足目标函数的最优控制效果,但随着流动模型的引入,随之而来的建模精度、未建模动态等问题也会出现,固定的流动模型也会限制控制系统的自适应能力。针对翼型在跨声速流动中遇到的激波抖振问题,为了消除不同来流状态的激波抖振带来的脉动载荷,开展了基于数据驱动方法的无模型自适应控制。流场数值仿真采用URANS方法,作动机构采用尾缘舵面,以升力系数作为反馈信号。当流动状态变化时,无模型自适应控制利用输入输出数据在线将流动系统等价转化为动态线性化数据模型,最小化性能指标得到控制律,使系统自动地工作于最优或接近最优的状态。时域仿真结果显示,无模型自适应控制效果优于开环控制和比例控制,并且当来流状态随时间发生变化时,无模型自适应控制也能够完全消除抖振脉动载荷。 | 任凯 高传强 张伟伟 | 2021 | 空气动力学学报2021，39，6： | 1 |
| 19 | Analysis of the dominant frequency in a subsonic compressor stator at near stall condition显示文摘IDDES method was applied to investigate the highly unsteady flow in a subsonic compressor stator with very large hub clearance and high incidence angle.The blade loading variation frequency was found close to the rotating instability(RI)frequency f RI&333 Hz observed in the experiment.Detailed analysis of the flow physics shows that the loading variation is caused by the periodic swing of the large scale separated flow on the blade suction side surface.The breakdown of the leakage vortex has no significant dominant frequencies,thus cannot be the cause of RI in this compressor stator as normally believed.Furthermore,the vortex shedding and vortex breakdown due to shear layer instability at the outer edge of the blade suction surface separation region excite high frequency unsteadiness that can form the sources of noise. | Ke Shi Song Fu | 2014 | Chinese Science Bulletin2014，59，1： | 0 |
| 20 | IDDES-SPOM方法高精度预测空天飞行器激波边界层干扰非定常局部分离流动显示文摘空天飞行器在执行飞行任务时,飞行马赫数范围较大,常处于超声速或高超声速状态,会面临激波/边界层干扰(SWBLI)等引起的复杂气动力、热等难题,其局部分离存在强压力脉动、高热流冲击等极端动载荷。针对空天飞行器沿程复杂SWBLI干扰引起的非定常局部分离流动,结合RANS高效率模拟近壁流动和LES高精度解析分离的RANS-LES混合方法是极具工程应用潜力的方法。然而,原始RANS-LES混合方法在预测大面积附体而局部分离的SWBLI流动时误差极大,需要在局部分离上游引入小扰动生成湍流结构,方能改善预测效果。以DES类IDDES方法为基础,在其SWBLI上游引入合成粒子组以获得湍流边界层,并应用IDDES-SPOM方法高精度数值仿真了空天飞行器典型部位SWBLI的非定常局部分离流动,包括压缩拐角、三维内流道和多面体等。揭示了激波振荡、局部压力脉动等非定常流动的产生和相互作用机制。该方法可预测空天飞行器典型部位的三维复杂非定常分离流动,预示其动载荷环境,为空天飞行器的结构设计提供理论支撑与分析手段。 | 杨益江 郭晓伟 肖志祥 | 2023 | 空天技术2023，，2： | 0 |
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