NACA 0012
A symmetric airfoil developed by NACA in the 1930s with a maximum thickness of 12% of the chord length. Its simple geometry and abundant aerodynamic data make it a classic benchmark for CFD validation.
Timeline (last 90 days)
The validation object is the NACA 0012 airfoil from NASA's turbulence modeling resource, with a Reynolds number of 6 million, the k-omega SST turbulence model, airfoil coordinates and wind tunnel data taken from NASA's results computed with CFL3D, 8 files in total.
The coarse-mesh computation at 10 degrees angle of attack yielded a lift of 1.077, versus CFL3D's 1.0778, a deviation on the order of one-thousandth.
The stall angle of attack was predicted to be 7 degrees, consistent with the wind tunnel, but the maximum lift is lower than the wind tunnel result because the SST model cannot simulate the sudden stall in the wind tunnel.
In the NACA 0012 airfoil verification task, the lift coefficient computed by the Agent on the coarse mesh at 10 degrees angle of attack was 1.077, within the error band of CFL3D's 1.0778.
In the result comparison, the suction peak at 10 degrees angle of attack differs from wind tunnel/CFL3D data by only 0.2%, the lift curve slope differs by 0.8%, and the stall angle of attack of 7 degrees matches the wind tunnel, but the maximum lift coefficient is low.
The NACA 0012 airfoil is a symmetric airfoil developed by NACA in the 1930s with a maximum thickness of 12% of the chord, and is a classic benchmark for CFD validation.
All Facts (6)
In the result comparison, the suction peak at 10 degrees angle of attack differs from wind tunnel/CFL3D data by only 0.2%, the lift curve slope differs by 0.8%, and the stall angle of attack of 7 degrees matches the wind tunnel, but the maximum lift coefficient is low.
60%UnverifiedThe validation object is the NACA 0012 airfoil from NASA's turbulence modeling resource, with a Reynolds number of 6 million, the k-omega SST turbulence model, airfoil coordinates and wind tunnel data taken from NASA's results computed with CFL3D, 8 files in total.
50%UnverifiedThe coarse-mesh computation at 10 degrees angle of attack yielded a lift of 1.077, versus CFL3D's 1.0778, a deviation on the order of one-thousandth.
50%UnverifiedThe stall angle of attack was predicted to be 7 degrees, consistent with the wind tunnel, but the maximum lift is lower than the wind tunnel result because the SST model cannot simulate the sudden stall in the wind tunnel.
50%UnverifiedIn the NACA 0012 airfoil verification task, the lift coefficient computed by the Agent on the coarse mesh at 10 degrees angle of attack was 1.077, within the error band of CFL3D's 1.0778.
50%UnverifiedThe NACA 0012 airfoil is a symmetric airfoil developed by NACA in the 1930s with a maximum thickness of 12% of the chord, and is a classic benchmark for CFD validation.
50%