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Model Development for a Comparison of VTOL and STOL Electric Aircraft Using Geometric Programming 用几何规划建立垂直起降与垂直起降电动飞机模型
Pub Date : 2019-09-04 DOI: 10.2514/6.2019-3477
C. Courtin, R. Hansman
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引用次数: 5
Multi-fidelity efficient global optimization: Methodology and application to airfoil shape design 多保真度高效全局优化:翼型外形设计的方法与应用
Pub Date : 2019-06-21 DOI: 10.2514/6.2019-3236
M. Meliani, N. Bartoli, T. Lefebvre, M. Bouhlel, J. Martins, J. Morlier
Predictions and design engineering decisions can be made using a variety of informa- tion sources that range from experimental data to computer models. These information sources could consist of different mathematical formulations, different grid resolutions, dif- ferent physics, or different modeling assumptions that simplify the problem. This leads to information sources with varying degrees of fidelity, each with an associated accuracy and querying cost. In this paper, we propose a novel and flexible way to use multi-fidelity informa- tion sources optimally in the context of airfoil shape optimization using both Xfoil and ADflow. The new developments are based on Bayesian optimization and kriging metamodeling and allow the aerodynamic optimization to be sped up. In a constrained optimization example with 15-design variables problem, the proposed approach reduces the total cost by a factor of two compared to a single Bayesian based fidelity optimization and by a factor of 1.5 compared to sequential quadratic programming.
预测和设计工程决策可以使用各种信息源,从实验数据到计算机模型。这些信息源可以由不同的数学公式、不同的网格分辨率、不同的物理特性或简化问题的不同建模假设组成。这导致信息源具有不同程度的保真度,每个信息源都具有相关的准确性和查询成本。在本文中,我们提出了一种新颖而灵活的方法,在翼型形状优化的背景下,同时使用Xfoil和ADflow优化多保真度信息源。新的发展是基于贝叶斯优化和克里格元模型,使气动优化速度加快。在具有15个设计变量的约束优化示例中,所提出的方法与基于贝叶斯的保真度优化相比,总成本降低了2倍,与顺序二次规划相比,总成本降低了1.5倍。
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引用次数: 22
Weak Non-Parallel Effects on Chemically Reacting Hypersonic Boundary Layer Stability 化学反应高超声速边界层稳定性的弱非平行效应
Pub Date : 2019-06-21 DOI: 10.2514/6.2019-2853
L. Zanus, F. M. Miró, F. Pinna
Advancing towards the correct modeling and subsequent understanding of laminar-toturbulent transition during atmospheric reentry is paramount for the future of aerospace technology. The coexistence of multiple physical phenomena and the grand amount of conditioning factors require the progressive extension of the applicability capabilities of the theoretical models. Past efforts have been mostly dedicated to investigate high-temperature and non-equilibrium effects using parallel stability theories. However, the implications of coupling these thermochemical phenomena with non-parallelism remains uncertain. Advanced state of the art thermodynamic and transport models are employed both in parallel and weakly non-parallel stability theories (LST and LPSE). A parametric study about the influence of nonlocal effects under different re-entry conditions and flow assumptions (i.e. CPG, TPG, CNE and LTE) showed that non-parallel effects stabilize/destabilize the boundary-layer, depending on the altitude and independently from the gas model employed. Particularly, they lead to a stronger destabilization of the 2nd Mackmode at the earliest points of the atmospheric re-entry flight envelope, reducing their effect until being weakly stabilizing at the lowest altitudes. Drastic N factor increments occurred assuming LTE, due to the presence of unstable supersonic modes, promoted by the boundary-layer cooling, caused by the intense chemical activity.
推进对大气层再入过程中层流到湍流过渡的正确建模和后续理解,对航空航天技术的未来至关重要。多种物理现象的共存和大量的制约因素要求理论模型的适用能力逐步扩展。过去的努力主要是利用平行稳定性理论来研究高温和非平衡效应。然而,将这些热化学现象与非平行性耦合的含义仍然不确定。并行和弱非并行稳定性理论(LST和LPSE)采用了最先进的热力学模型和输运模型。一项关于不同再入条件和流动假设(即CPG、TPG、CNE和LTE)下非局部效应影响的参数化研究表明,非平行效应会使边界层稳定/不稳定,这取决于海拔高度,与所采用的气体模型无关。特别是,它们在大气层再入飞行包线的最早点导致第2马克模更强的不稳定,减少它们的影响,直到在最低高度弱稳定。假设LTE发生剧烈的N因子增量,由于边界层冷却促进了不稳定超音速模式的存在,这是由强烈的化学活动引起的。
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引用次数: 7
Jacobian-free implicit p-adaptive high-order compact direct flux reconstruction methods for unsteady flow simulation 非定常流动模拟的无雅可比隐式p自适应高阶紧致直接通量重建方法
Pub Date : 2019-06-17 DOI: 10.2514/6.2019-3062
Lai Wang, Meilin Yu
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引用次数: 4
Correction: Hypersonic wake measurements behind a slender cone using FLEET velocimetry 修正:使用FLEET测速仪测量细长锥体后面的高超声速尾迹
Pub Date : 2019-06-17 DOI: 10.2514/6.2019-3381.C1
Yibin Zhang, Daniel R. Richardson, S. Beresh, Katya M. Casper, M. Soehnel, J. Henfling, R. Spillers
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引用次数: 0
Global instability analysis of a boundary layer flow over a small cavity 小空腔上边界层流动的全局不稳定性分析
Pub Date : 2019-06-17 DOI: 10.2514/6.2019-3535
M. Mathias, M. Medeiros
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引用次数: 3
Textile Strain Measurement System 纺织品应变测量系统
Pub Date : 2019-06-17 DOI: 10.2514/6.2019-3146
A. Witkowski, A. Levay, M. Murbach
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引用次数: 1
Nonlinear Görtler Vortices and Their Secondary Instability in a Hypersonic Boundary Layer 高超声速边界层中的非线性Görtler涡旋及其二次不稳定性
Pub Date : 2019-06-17 DOI: 10.2514/6.2019-3216
Fei Li, Meelan Choudhari, P. Paredes
Nonlinear development of the Görtler instability over a concave surface gives rise to a highly distorted inflectional flow field in the boundary layer that leads to both wall-normal and spanwise gradients in the flow. Such nonlinear structures are susceptible to strong, high-frequency secondary instabilities that may lead to the onset of laminar-turbulent transition. The present numerical study uses direct numerical simulations and linear secondary instability theory to investigate finite amplitude Görtler vortices and their secondary instability characteristics, respectively, in the hypersonic flow over an axisymmetric cone with a concave aft body. To complement previous studies in the literature wherein the Görtler instability was usually studied for a flat plate and initiated at some upstream location by imposing an eigenfunction as the inflow condition or by blowing and suction at the wall, the present investigation is focused on fully realizable Görtler instability that is excited by an azimuthally periodic array of surface protuberances. Furthermore, while the previous work had mostly focused on the secondary instability of Görtler vortices with cross-plane velocity contours that resembled bell-shaped structures, the present results confirm that fully developed mushroom structures also exist in the hypersonic regime when the Görtler vortex amplitude is sufficiently large. Computations further reveal that the dominant modes of secondary instability in these mushroom-shaped structures correspond to an antisymmetic (i.e., sinuous) “stem” mode that concentrates within the strong, nearly wall-normal internal shear layers surrounding the stem regions underneath the caps of the mushroom structures. Additionally, there exist a multitude of other significantly unstable secondary instability modes of both symmetric and antisymmetric types. Analogous to the secondary instability of crossflow vortices in hypersonic flows, secondary instability modes originating from the Mack mode instability play an important role during the nonlinear breakdown process.
在凹表面上Görtler不稳定性的非线性发展会在边界层中产生高度扭曲的弯曲流场,从而导致流动中的壁向和展向梯度。这种非线性结构容易受到强的、高频的二次不稳定性的影响,这可能导致层流-湍流过渡的发生。本文采用直接数值模拟和线性二次不稳定性理论,分别研究了有限幅值Görtler涡旋及其二次不稳定性特征。先前的文献研究中,通常研究平板的Görtler不稳定性,并通过施加特征函数作为流入条件或在壁面上吹吸而在上游位置启动,为了补充这些研究,本研究的重点是由表面凸起的方位角周期性阵列激发的完全可实现的Görtler不稳定性。此外,虽然以前的工作主要集中在具有类似钟形结构的跨平面速度轮廓的Görtler涡的二次不稳定性上,但目前的结果证实,当Görtler涡幅值足够大时,高超声速区也存在完全发育的蘑菇结构。计算进一步揭示,在这些蘑菇状结构中,次要不稳定的主要模式对应于反对称(即弯曲)“茎”模式,该模式集中在蘑菇结构帽下围绕茎区域的强大的、接近壁法向的内部剪切层内。此外,存在大量其他显著不稳定的对称和反对称型的二次不稳定模态。与高超声速流中横流涡的二次不稳定类似,源自Mack模态不稳定的二次不稳定模态在非线性击穿过程中起着重要作用。
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引用次数: 5
Correction: Implicit Large Eddy Simulation of Low Pressure Turbine Airfoils Using a High Order Navier-Stokes Solver 修正:使用高阶Navier-Stokes求解器的低压涡轮翼型的隐式大涡模拟
Pub Date : 2019-06-17 DOI: 10.2514/6.2019-2840.C1
M. Bolinches-Gisbert, R. Corral, F. Gisbert, A. Sotillo
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引用次数: 0
F-35 High Angle of Attack Flight Control Development and Flight Test Results F-35大迎角飞行控制研制及飞行试验结果
Pub Date : 2019-06-17 DOI: 10.2514/6.2019-3227
Dan Canin
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引用次数: 3
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AIAA Aviation 2019 Forum
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