SAMPLES

 

3D flow

·      Mach 1.6 flow past a blunt-nose-cylinder projectile at 4o angle of attack (NASA-TMX-3558).

·      Mach 1.2 flow past an ellipse-cylinder projectile at 8o angle of attack.

·      Mach 1.4 flow past a 4% circular bump.

·      Mach 1.4 flow past a sphere.

·       Generating 3D finite element mesh for canard-wing-tail-body combination.

·       Canard-wing-tail-body combination meshes generation (1).

·       Canard-wing-tail-body combination meshes generation (2).

·       Mach 1.2 flow passes canard-wing-tail-body at 10o angle of attack.

·       Mach 1.2 flow past the elliptical rocket at 10 degrees angle of attack.

 

3D Conical flow

·       Mach 1.8 flow passes a 5o cone at 45o angle of attack.

·       Mach 7.4 flow past a 75o swept ellipse cone at 15o angle of attack.

 

2D Axisymmetric Flow

·       Mach 1.76 shock wave out of a cylindrical tube.

·       Flow discharges from a 25o or 45 o convergent nozzles with P/P¥=4.0.

·       Mach 0.94, 0.96 and 1.2 flow past a secant-ogiv-cylinder-boattail projectile.

·       Mach 1.6, 2.3, 4.63 flow past an circular-arc-cylinder-flare projectile with Reynolds number equal to 6.6x106.

·      Mach 1.6, 2.3, 4.63 flow past an circular-arc-cylinder-boattail projectile with Reynolds number equal to 6.6x106. NASA-TMX-3558

 

 

2D planar flow

·      Mach 1.2 flow past a NACA0012 airfoil at 0o angle of attack

·      Mach 1.2 flow past a NACA0012 airfoil at 7o angle of attack

 

1D, planar, cylindrical and spherical flows

·      Transient Solution at 6.1 m Second for The Sod’s Shock Tube.

·      Reflection of a Cylindrical Convergent Shock Wave.

·      Helium Exploded Into Surrounded Air.

 

Chemical reacting flows

·       g2-Spherical-Helium-explodes

·       g3-Transverse-He-Injection

·       g4-Ramped-duct-recation

·       g5-H2-blast-wave

·       g6-deonation