Transonic Tail Buffet Simulations for the Common Research Model
Transonic Tail Buffet Simulations for the Common Research Model
复制标题
通用研究模型的跨音速尾部抖振模拟
DOI：
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发表时间：
2013
期刊：
影响因子：
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通讯作者：
E. Kraemer
中科院分区：
文献类型：
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作者：
S. Illi;Christian Fingskes;T. Lutz;E. Kraemer
在 2014 年欧洲跨音速风洞 ESWI RP 测量活动之前，使用 DLR TAU 代码对 NASA 通用研究模型进行了数值模拟。所提出的研究重点是高马赫数下主翼分离流与水平尾翼之间的相互作用。这种现象被称为跨音速尾部抖振，会带来严重的风险，因此限制了商用飞机的飞行包线。构建了 CRM 网格，其中包括高分辨率四面体块，以减少尾流中的耗散效应。进行的验证显示与阻力预测研讨会的结果非常一致。基于升力极模拟，定义了抖振起始状态，并选择了超出该点的流入条件来执行非定常模拟。结果表明，角分离导致主翼上表面复杂激波系统的运动。大涡流散落，向下游传播并极大地影响 HTP 周围的流动，随后在所有积分系数中发现高频响应。
In advance of the ESWI RP measurement campaign in the European Transonic Wind Tunnel in 2014, numerical simulations for NASA’s Common Research Model were performed using the DLR TAU code. The presented investigations are focused on the interaction between the separated flow of the main wing with the horizontal tail plane at high Mach numbers. This phenomenon, called transonic tail buffet, poses a serious risk and therefore limits the flight envelope for commercial aircraft. A mesh for the CRM was built including a high resolved tetrahedral block to reduce dissipative effects in the wake. A validation was conducted which shows excellent agreement to the results of the Drag Prediction Workshops. Based on lift polar simulations the buffet onset regime was defined and an inflow condition beyond this point was selected to perform an unsteady simulation. It is shown that a corner separation leads to a movement of the complex shock system on the upper surface of the main wing. Large vortices are shed which propagate downstream and massively influence the flow around the HTP followed by a high frequency response which is found in all integral coefficients.