The transonic airfoil test case, airfoil RAE2822, was calculated using the NSMB (Navier-Stokes Multi-Block) code. It is a finite-volume code for structured grids, solving the compressible Navier-Stokes equations. The calculations were performed using the k —τ model with two different sets of...
Accuracy of BGK scheme in solving viscous transonic turbulent flow over the airfoil will be examined. Results obtained from the computations are also compared with experimental data and will demonstrate that a very good agreement has been achieved.Ong J. Chit...
Transonic flow over the RAE2822 airfoil has been solved for flow coditions corresponding to the AGARD test case 10. An extensively tested steady Navier-Stokes flow solver based on the finitevolume cell-centered explicit Runge-Kutta time stepping scheme has been used to simulate the flow. The ...
This paper presents a second moment closure Reynolds stress turbulence model implementation applied to a simulation of a well known transonic airfoil flow case (RAE2822). Comparisons are made between simpler turbulence models and the present implementation regarding its ability to predict the shock ...
fluent 验证案例17:Transonic Flow over an RAE 2822 Airfoil 跨音速流动在rae2822翼型 流过一个rae2822翼型在自由流马赫数0.73。迎角为2.79°。流场是二维的、可压缩的(跨音速)和湍流的。 使用了基于密度的求解器的隐式公式。使用SST k-ω湍流模式来解释湍流效应。
Transonic buffet control research with two types of shock control bump based on RAE2822 airfoil超临界翼型冲击控制跨音速抖振控制Stokes空气动力学特性类型激波强度Current research shows that the traditional shock control bump(SCB) can weaken the intensity of shock and better the transonic buffet ...
Computational Study of Transonic Flow over a RAE- 2822 Airfoil by Using FLUENT CodeAbaas Ali Abud Al-Nabi
Aerodynamic characteristicLift coefficientMoment coefficientAn experimental study of pressure distributions over RAE2822 airfoil in the two-dimensional test section 0.8脳0.4 meter of a transonic wind tunnel which is the first pressruized continuous wind tunnel in China is presented. This paper in order ...
The article presents results of a numerical solution of subsonic, transonic and supersonic flows described by the system of Euler equations in 2D compressible flows around the RAE 2822 airfoil. Authors used FVM multistage Runge-Kutta method to numerically solve the flows around the RAE 2822 airfoil...
FFD (free-form deformation) technique was applied to achieve the parameterization of RAE2822 transonic airfoil. Then the method of DoE (design of experiment) was used to obtain the sample values of design parameters by CFD (computational fluid dynamics) numerical simulation. Lastly, the optimization...