Unsteady shock front waviness in shock-buffet of transonic aircraft  

作　　者：Razvan Marian Apetrei Vlad Ciobaca Jose Luis Curiel-Sosa Ning Qin 

机构地区：[1]Department of Mechanical Engineering,The University of Sheffield,Sheffield,UK [2]DLR,Institute of Aerodynamics and Flow Technology,Braunschweig,Germany

出　　处：《Advances in Aerodynamics》2020年第1期182-198,共17页空气动力学进展（英文）

基　　金：The authors would like to acknowledge the University of Sheffield for funding of the project through a PhD studentship to the first author.This project has also been supported through an additional funding received via the Postgraduate Researcher Experience Programme(PREP)from the same institution.

摘　　要：The unsteady transonic aerodynamics of a wing-body configuration is investigated by solving the Unsteady Reynolds-averaged Navier-Stokes equations closed with the full Reynolds Stress Model.This work presents the prediction of flow field characteristics during deep shock-buffet penetration of a transport aircraftrepresentative geometry.Mach number of 0.85,and Reynolds number of 5 million based on the mean chord,are selected to reproduce experimental test conditions that serve as validating datasets.The results obtained give information about both surface and flow field shock-buffet dynamics.An unsteady shock front is observed on the suction side of the wing which gives birth to the so-called buffet cells.Flow field characteristics are dominated by the presence of lambda-shaped shocks and fully separated boundary layer over a significant part of the wing.

关 键 词：AERODYNAMICS CFD Shock-buffet 

分 类 号：O35[理学—流体力学]