基于混合雷诺平均/高精度隐式大涡模拟方法的高升力体气动噪声模拟

Aeroacoustic simulation of the high-lift airfoil using hybrid reynolds averaged Navier-Stokes/high-order implicit large eddy simulation method

发展了基于七阶精度混合型耗散紧致格式(HDCS)的混合雷诺平均(RANS)/高精度隐式大涡模拟(HILES)模型(HRILES),并结合Ffowcs Williams-Hawkings(FWH)声比拟方法对30P30N高升力体气动噪声问题进行了模拟.首先对雷诺数Red=4.3×10^4的单圆柱绕流算例开展验证,并与传统的延迟分离涡模拟(DDES)模型进行对比.结果表明HRILES模型具有对亚临界态尾迹区转捩流动的模拟能力,平均阻力系数与阻力均方根值和实验结果符合更好,结合FWH声比拟方法得到了合理的远场声压级(SPL)的功率谱密度(PSD)分布.然后将其应用于30P30N高升力体气动噪声算例模拟,结果表明HRILES模型准确预测缝翼凹腔剪切层各站位的平均速度、涡量和湍动能分布,壁面脉动压力谱分布与实验符合较好,近、远场噪声频谱准确预测了缝翼低频窄带噪声,并得到了合理的噪声辐射指向性分布.

A hybrid RANS/HILES method(HRILES)is developed by combining the RANS-SST model and high order implicit large eddy simulation method(HILES)and employed with the Ffowcs Williams-Hawkings(FWH)equation to predict the slat noise of 30P30N high-lift airfoil.Comparison has been made between the HRILES method and the traditional DDES based on the full-turbulence model SST by simulating the single cylinder case with Red = 4.3 × 10^4.The HRILES method is able to predict the transition phenomenon and the small-scale separation bubble in the sub-critical wake region while the DDES can’t and get a better mean wall pressure distribution than DDES.The amplitude and frequency spectrum of the far-field sound pressure level are in good agreement with the experimental data.In the simulation of 30P30N high-lift airfoil,the famous IDDES model is also used for comparison,both results are compared with experimental measurements.The computational mesh is provided by Japan Aerospace Exploration Agency(JAXA)in the Workshop on Benchmark problems for Airframe Noise Computations(BANC).The HRILES method obtains quantitative agreement with experimental data in terms of mean wall pressure coefficient,frequency spectrum of pressure fluctuations on the slat surface,and the mean flow statistics in the slat cusp shear layer.The IDDES model slightly underestimate the suction effect on the upper surface of the slat,and delays the instabilities in the slat cusp shear layer.The near-field noise spectra are compared with measurements obtained in JAXA low-speed Wind Tunnel.Narrow band peaks present are well recovered by both methods,while IDDES model overestimate the broadband noise.Far-field noise directivity results of every components,filtered in the band[256 Hz-10 KHz],are compared with each other,and the slat cove is confirmed to dominate the sound noise levels.The slat and flap noises show a typical dipole distribution,while the main wing noise’s directivity is not apparent.Computational results show that the HRILES method,as one kind of generalized Hybrid RANS/LES method,HRILES can smoothly switch between the SST model and the HILES method.HRILES has the highresolution simulation capability of the HILES in the LES region,and can reduce the requirements of the HILES method on the near-wall grid distribution by using the SST model in the inner boundary layer.As a result,the HRILES method has advantages in simulations at high reynolds numbers and aeroacoustic problems.Further research will be carried out in the applications at higher reynolds number flows with complex geometry in the future.