CFD data

2D subsonic case: NACA 0012 airfoil

This is a 2D low-speed high-angle of attack case:

• Info for Epsilon Aero Data:
Solver: Fluent (RANS + SA turbulence + Energy equation)
Angle of attack = 10 °
M = 0.3
Ps0 = 101325 Pa
Ts0 = 288 K
C = 0.435 m

• Download files:
NACA 0012_M03_AoA10
_{(Required RAM: 3GB)}

2D transonic case: NACA 0012 airfoil

This is a 2D high-speed low-angle of attack case:

• Info for Epsilon Aero Data:
Solver: Fluent (RANS + SA turbulence + Energy equation)
Angle of attack = 0°
M = 0.8
Ps0 = 101325 Pa
Ts0 = 288 K
C = 0.435 m

• Download files:
NACA 0012_M08_AoA0
_{(Required RAM: 3GB)}

3D subsonic case: Rectangular wing (AR=8/NACA 0012)

This is a 3D low-speed high-angle of attack case:

• Info for Epsilon Aero Data:
Solver: Fluent (RANS + SA turbulence + Energy equation)
Angle of attack = 10°
M = 0.3
Ps0 = 101325 Pa
Ts0 = 288 K
Sref = 0.7569 m^2
C = 0.435 m

• Download files:
WING_M03_AoA10
_{(Required RAM: 32GB)}

3D transonic case: Rectangular wing (AR=8/NACA 0012)

This is a 3D high-speed low-angle of attack case

• Info for Epsilon Aero Data:
Solver: Fluent (RANS + SA turbulence + Energy equation)
Angle of attack = 2.5°
M = 0.8
Ps0 = 101325 Pa
Ts0 = 288 K
Sref = 0.7569 m^2
C = 0.435 m

• Download files:
WING_M08_AoA2_5
_{(Required RAM: 32GB)}