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首页> 外文会议>AIAA/CEAS aeroacoustics conference;AIAA aviation forum >SWAHILI: an experimental aerodynamic and acoustic database of a 2D high lift wing with sweep angle and flap side edge
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SWAHILI: an experimental aerodynamic and acoustic database of a 2D high lift wing with sweep angle and flap side edge

机译：SWAHILI：具有扫掠角和襟翼侧边缘的二维高升力机翼的实验空气动力学和声学数据库

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In the SWAHILI (SWept Airfoil with High LIft) Onera-DLR Common Research Project (CRP), both research centers are building an experimental database for the validation of CFD/CAA codes applied to the simulation of the unsteady flow and noise generation from a high-lift profile with deployed slat and flap and a global sweep angle of 30°. The project is based on DLR's model F16, a two-dimensional airfoil (constant section in the span direction), with a 300 mm clean (retracted) chord. This project is a continuation of the LEISA2 (Silent Take-Off and Landing, 2010-2013) project, in which a similar database has been built with the same model, but without sweep angle. Since 2014, the LEISA2 test-case has been included by NASA and AIAA in the Benchmark for Airframe Noise Computations (BANC). In both projects LEISA2 and SWAHILI, the model has been tested in F2, an aerodynamic wind tunnel located in Onera-Le Fauga, with intensive aerodynamic measurements, including steady/unsteady wall pressure sensors, optical devices such as PIV and steady/unsteady LDV and a hot wire probe. Acoustic measurements were also achieved in F2 with a wall microphone array mounted in the windtunnel ceiling. During the SWAHILI project, Dassault-Aviation has partnered with Onera and DLR, contributing to the project with two additional configurations of flap side edge, with the same aerodynamic and acoustic measurements in F2. In LEISA2 the un-swept model has been also tested in AWB, an anechoic open-jet wind tunnel located in DLR-Braunschweig for acoustic data acquisition. In the SWAHILI context, similar tests are under progress with the SWAHILI swept model. The present paper focusses on the influence of the sweep angle and the flap side edge on the characteristics of the unsteady flow and on the radiated noise.
机译：在SWAHILI（高升空后掠翼型飞机）Onera-DLR共同研究项目（CRP）中，两个研究中心都在建立一个实验数据库，以验证CFD / CAA代码的有效性，该代码可用于模拟从高处产生的非稳态流动和噪声展开的轮廓，带有展开的板条和襟翼，整体后掠角为30°。该项目基于DLR的F16模型，这是一个二维翼型（翼展方向上的恒定截面），弦长为300毫米（净弦）。该项目是LEISA2（静音起飞和着陆，2010-2013）项目的延续，在该项目中，已使用相同的模型构建了相似的数据库，但没有后掠角。自2014年以来，LEISA2测试用例已被NASA和AIAA纳入“机身噪声计算基准”（BANC）。在LEISA2和SWAHILI项目中，该模型均已在F2（位于Onera-Le Fauga的空气动力学风洞）中进行了测试，并进行了密集的空气动力学测量，包括稳定/不稳定壁压传感器，光学装置（例如PIV）和稳定/不稳定LDV和一个热线探针。在F2中，通过在风洞顶棚中安装壁挂麦克风阵列也可以实现声学测量。在SWAHILI项目期间，达索航空与Onera和DLR合作，为该项目提供了两个附加的襟翼侧边缘配置，在F2中具有相同的空气动力学和声学测量。在LEISA2中，未扫描的模型也已在AWB中进行了测试，AWB是位于DLR-布伦瑞克的消声开放式风洞，用于获取声学数据。在SWAHILI环境中，SWAHILI扫描模型正在进行类似的测试。本文着眼于后掠角和襟翼侧边缘对非稳态流动特性和辐射噪声的影响。

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