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CFD Verification & Validation Data

This page presents a set of relevant CFD and experimental data for verification and validation of CFD codes. Both two-dimensional and three-dimensional solutions are available and are labelled as 2D and 3D repsectively. Pseudo-2D solutions, two-dimensional problems solved in three-dimensions by adding a non-zero thickness, are labelled as 2D*. All CFD solutions are performed with the new STARS CFD solver currently under development in our lab, which is a space-time finite element solution to the compressible Euler equations in a non-inertial frame.

Verification Data

In the field of computational fluid dynamics, verification is typically referred to as solving the equations right. In adopting that definition, the verification solutions provided below attempt to demonstrate that our governing equations, the compressible Euler equations, are solved correctly by comparing our CFD solution to the analytic solution for each problem.

Validation Data

Validation solutions are intended to demonstrate that the relevant flow physics are modeled correctly by a CFD solution for a particular application of interest. To this end, the validation solutions provided below are a sampling of aerospace applications where a numerical solution for the compressible Euler equations is an accurate approximation to the dominant flow physics. These problems differ from the preceding verification solutions in that the ultimate comparison is with experimental data.

Experimental Data

We have a limited set of experimental data that can be downloaded here. As a general rule, we don't do experimental work, so most or all of this data was pulled from the engineering literature for validation of our own CFD work. For all such data, the original references will be listed in case you have any questions about the experiment. Please do not E-mail us with questions about these experiments. Refer to the original references and/or authors for such questions.

  • 80° Delta Wing: Steady pressure distribution data for an 80° delta wing at a pitch angle of 30° and various roll angles in an incompressible flow.
  • BACT Wing: Steady pressure distribution data for the Benchmark Active Controls Technology Wing at zero angle of attack for Mach numbers ranging from 0.51 to 0.82.
  • Hovering Rotor: Chordwise pressure distribution data and blade spanwise load distribution data for a hovering rotor with an aspect ratio of 6.0 at various collective pitch angles and angular velocities.

Revised: March 20, 2001 [TJC]
Oklahoma State University