To simulation of laminar compressible
flow, velocity is 0.3 mach, angle of attack is 2.0 degree, Re equal 10E6, total
temperature is 
and laminar Prandtle number is 0.72. Obtained results which
have well agree, was compared with experiment and shown.
Turbulent compressible flow field simulation.
For turbulent compressible
flow we solved flow field around airfoil NACA0012 at mach number 0.502 and angle
of attack is 1.77 degree. Obtained results were compared with and shown. Also
simulation of turbulent compressible flow around airfoil INT_7k (Russian
standard) with mach 0.333 and angle of attack 10 degree, was shown.
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MACH Contours for NACA0012 airfoil (M=0.3 laminar).
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Pressure Coefficient Contours for NACA0012 airfoil (M=0.3 laminar).
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Velocity vector on leading edge of naca0012 airfoil (M=0.3 Laminar)
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Velocity vector on trailing edge of naca0012 airfoil (M=0.3 Laminar).
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Comparison of calculated and experimental pressure distributions for the NACA0012 airfoil (M=0.3 laminar).
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MACH Contours for INT_7K airfoil (M=0.333 Turbulent).
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Pressure Coefficient Contours for INT_7K airfoil (M=0.333 Turbulent).
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Velocity vector on leading edge of INT_7K airfoil (M=0.333 Turbulent).
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Velocity vector on trailing edge of INT_7K airfoil (M=0.333 Turbulent).
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Pressure Distribution on INT_7K airfoil (M=0.333 Turbulent).
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MACH Contours for NACA0012 airfoil (M=0.502 Turbulent). |
Pressure Coefficient Contours for NACA0012 airfoil (M=0.502 Turbulent). |
Velocity vector on leading edge of naca0012 airfoil (M=0.502 Turbulent) |
Velocity vector on trailing edge of naca0012 airfoil (M=0.502 Turbulent) |
Comparison of calculated and experimental pressure distributions for the NACA0012 airfoil (M=0.502 Turbulent). |
