SAMPLES

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.

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

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-ogive-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

3D Conical flow

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

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

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 8^o 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 10^o angle of attack.

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

• Mach 0.4, 0.9 and 1.4 flow past a cone-cylinder-wing combination at 10^o angle of attack.
• Mach 1.2 and 0.2 flow passes the Javelin rocket at 10 and 5 degrees angle of attack.
• Mach 1.2 and 0.95 flows pass the Arconi-Hi rocket at 10 and 5 degrees angle of attack.
• Mach 1.2 and 0.95 flows past the Arconi-Hi with tail ring rocket at 10 and 5 degrees angle of attack.