CFL3D
A structured-grid computational fluid dynamics (CFD) solver developed at NASA Langley, whose cases are often used as numerical benchmarks.
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 prompt set acceptance criteria of lift deviation within 2% from CFL3D and a grid independence verification across three meshes.
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.
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.
CFL3D is a structured-grid CFD solver developed by NASA Langley, and its cases are often used as numerical benchmarks.
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 prompt set acceptance criteria of lift deviation within 2% from CFL3D and a grid independence verification across three meshes.
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%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%UnverifiedCFL3D is a structured-grid CFD solver developed by NASA Langley, and its cases are often used as numerical benchmarks.
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