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Turbulent Flat Plate

Figure 1 Diagram is described in the surrounding text
Figure 1. Computational domain for the turbulent flat plate flow case.

Flow Description

This case examines Mach 0.2 flow over a flat plate. The flow conditions are summarized in Table 1. The flow becomes turbulent on the flat plate.

Table 1. Freestream conditions. 
Mach Pressure (psia) Temperature (R) Angle-of-Attack (deg) Angle-of-Sideslip (deg)
0.2 14.7 530.0 0.0 0.0


The geometry is the top surface of the plate with a length of 16.7 feet.

Comparison Data

The flow field being modeled is that reported by Wieghardt (1952) and later included in the 1968 AFOSR-IFP Stanford Conference, Coles and Hirst (1969). The data can be accessed through Table 2. To accelerate the convergence rate of these compressible flow solvers for this case, the freestream Mach number was set to 0.20.

Table 2. Experimental Data.

Computational Studies

Table 2. Computational studies peformed for the turbulent flat plate case.
Study Category Person Comments
Study #1 Model D.A. Yoder Turbulence model and grid resolution study.
Study #2 Model N.J. Georgiadis Unstructured grid solution.


Coles, D.E., and Hirst, E.A., Computation of Turbulent Boundary Layers-1968 AFOSR-IFP-Stanford Conference, Vol. II, Stanford University, CA, 1969.

Patel, Virendra C., Rodi, Wolfgang, and Scheuerer, Georg, "Turbulence Models for Near-Wall and Low-Reynolds Number Flows: A Review," AIAA Journal, Vol. 23, No. 9, pp. 1308-1319, September 1985.

Wieghardt, K., and Tillman, W., "On the Turbulent Friction Layer for Rising Pressure," NACA TM-1314, 1951. [PDF]

Contact Information

Questions or comments about this case can be sent to the respective individuals performing the indicated studies. Otherwise comments can be emailed to John W. Slater at the NASA Glenn Research Center.

Last Updated: Wednesday, 10-Feb-2021 09:38:59 EST