C3.8 Common Research Model (DPW-5)

[source: http://aaac.larc.nasa.gov/tsab/cfdlarc/aiaa-dpw]


The common research model (CRM) is a wing-body configuration which was extensively studied with state-of-the-art CFD codes in the fifth drag prediction workshop (DPW-5).

The CRM is considered under transonic cruise conditions. The flow is assumed to be steady-state and fully turbulent. Computations are to be performed in a target lift mode, i.e., given a specified lift coefficient, the corresponding angle of attack has to be determined. The objective of the simulations is to obtain mesh-converged drag and moment coefficient values as well as pressure distributions in sections along the wing span.

Flow Conditions and Parameters

This study corresponds to the first test case of DPW-5.


A series of nested structured multi-block meshes has been generated for DPW-5 (cf. AIAA Paper 2011-3508) and is available in various formats as well as converted to several unstructured meshes including split elements.

The original sequence of structured meshes can be converted to high-order meshes with quartic edge representation, but these meshes exhibit strong oscillations at the wing tip and fairing-body junction. An alternative mesh has been provided by Marco Ceze, University of Michigan. The hexahedral mesh uses a piecewise cubic representation and thus a good geometry resolution, even though it is coarse enough (80k elements) to serve as starting point for adaptive algorithms. It is provided in GMSH format.

For reasons of comparability, all participants are motivated to use the provided mesh for computations. Computations on a mesh sequence should be performed by uniform refinement of the initial mesh. If participants cannot refine the mesh in their own codes, finer versions of the baseline mesh can be provided upon request.

Additional information

geometry reference for the CRM:

For further information, please refer to the DPW-5 web site and the references cited therein.


last modified: 2013/02/06, tobias.leicht@dlr.de