I did some projects about calculation of aerodynamic forces and flow field simulation around of airfoils, wings, missiles, airplane and RPV. by a CFD's Software. Some of these projects are presented below.
|
|
|
|
|
|
Flow Path Line around of NACA0015, Colored by Velocity magnitude.
|
Comparison Cl Between Recent Work (red), CFL3D and Experimental Data
|
|
|
|
|
Comparison Cd Between Recent Work (red), CFL3D and Experimental Data. |
Comparison Cm Between Recent Work (red), CFL3D and Experimental Data. |
|
|
|
|
Mach Contour on a Missile, M=0.85, Alpha=0.0.
|
Static Pressure Contour in Symmetry Plane and Missile, M=2.0, Alpha=15.0 (deg).
|
|
|
|
|
Velocity Vector at a section of Wing. V=50m/s, ALpha=26.0(deg).
|
Flow Path Line Colored by Velocity Magnitude at Tip of Wing, V=50m/s, ALpha=26.0(deg).
|
|
|
|
|
Comparison CL Between CFD (red), Wind Tunnel Data (blue) , V=50m/s.
|
Comparison CD Between CFD (red), Wind Tunnel Data (blue) , V=50m/s.
|
|
|
|
|
View of Grid Generation On Wing and Symmetry
Plane (Onera M6).
|
|
|
|
|
|
Static Pressure Contour on Wing and Symmetry Plane. M=0.84, Alpha=3.96.
|
Sonic Zone on Wing. M=0.84, Alpha=3.96.
|
|
|
|
|
Comparison Cp Between Recent Work (Inviscid and Turbulent), and Experimental Data. |
Comparison Cp Between Recent Work (Turbulent), and Experimental Data.
|
|
|
|
|
Geometry of Model.
|
Simulation Flow Field Around of Model in Supersonic Wind Tunnel Test Section.
|
|
|
|
|
Mach Contour on RPV. |
Flow Path Line Colored by Velocity Magnitude on RPV. |
