M219 supersonic outflow field

2024-03-20

There are multiple shock waves in the M219 supersonic flow field, and the adaptive grid encryption of the shock wave position is carried out in this example, which can better capture the shock wave...

RAE2822 stabilize the shock wave

2024-03-20

Under the condition of transonic velocity, shock waves are easy to form on the upper surface of the RAE2822 airfoil, which may cause flow separation under the interaction of shock waves and turbule...

S809 blades turbulent and transitioning

2024-03-20

The S809 is a typical low-speed wind airfoil, a 21% thick laminar airfoil designed by Dan M Somers for turbines, and the low-speed experiment was completed in the low turbulence wind tunnel of the ...

NACA0012 airfoil

2024-03-20

NACA 0012 is a classic airfoil that has been extensively studied and used. In this example, the angle of attack is 15 degrees, and most of the boundary layer is turbulent in the attached surface la...

Sphere Re3700 Sphere Circulation

2024-03-20

The three-dimensional spherical flow under the subcritical Reynolds number has obvious unsteady effects, and has the characteristics of thin laminar flow boundary layer, flow separation, shear lami...

Cylinder Re200 Cylinder Flow

2024-03-20

Under this Reynolds number, there is a classic Karmen vortex street phenomenon, and the tail vortex oscillates symmetrically periodically.Comparing the results of the conformal consistency grid and...

No sticky shock tubes

2024-03-20

The CDV advisco-free shock tube is a NASA standard verification study, and Dimaxer is used to solve the K1, K3&K4 transtone and ultrasonic conditions, which verifies the numerical stability of ...

Front and rear step flow with wedge angle double Mach reflection

2024-03-19

Pure natural flow solving, no iteration, no convergence problem, accurate capture of the shock wave development process.Pictured: Front and rear step flow and wedge Mach reflection

VKI-59

2024-03-13