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** Laminar Flat Plate **

## Laminar Flat Plate

**Figure 1. Geometric configuration for laminar flow past a
flat plate. **

### Flow Description

This validation case involves the flow past a flat plate at zero
angle of incidence. The Mach number of the flow is Mach 0.1, which can
be assumed "incompressible". A laminar boundary layer develops on the
plate and thickens along the plate.

**Table 1. Freestream conditions. **
Mach |
Pressure (psia) |
Temperature (R) |
Angle-of-Attack (deg) |
Angle-of-Sideslip (deg) |

0.1 |
6.0 |
700.0 |
0.0 |
0.0 |

These conditions were chosen so that the Reynolds number based on
the length of the plate (1.0 ft) was approximately 200000.

### Geometry

The flat plate has a length of 1.0 ft. The leading edge is located
at x = 0.0 ft.

### Computational Domain and
Boundary Conditions

At the flat plate surface the no-slip condition applies. The
inflow boundary of the computational domain is a subsonic inflow
boundary and is placed upstream of the leading edge at x = - 0.25 ft so
as to capture the leading edge flow. The outflow boundary is placed at
the end of the plate at x = 1.0 ft. The farfield flow beyond the
boundary layer should remain fairly uniform at freestream conditions.
The farfield boundary is placed at about eta = 50.

### Comparison Data

The classical Blasius similarity solution provides data for
comparison. The text by White discusses this solution.

The Fortran program blasius.f creates the
following data files for comparison. The solution for the similarity
equation is given in the file
fplam.blasius. The data files are
u.blasius, v.blasius, and cf.blasius.

### Computational Grid

The computational grid was generated by the Fortran program fpgrid.f. The grid points are evenly spaced along
the plate according to the streamwise grid spacing specified. The
normal grid points are placed at constant "eta" coordinates with the
grid evenly spaced until "eta" = 4.0 and then spaced by a factor of 1.1
until the outer boundary at "eta" = 50 is reached. Thus, the number of
streamwise and normal grid points are determined according to the
desired spacings. Fig. 2 below shows how the grid looks.

**Figure 2. Computational Grid (coarsened for display).**

### Computational Studies

** Table 2. Computational studies. **
Study |
Category |
Person |
Comments |

Study #1 |
Example |
J. Slater |
Single run |

### References

White, F.M., * Viscous Fluid Flow *, McGraw Hill
Inc., New York, 1974.

### Contact Information

Questions or comments about this case can be sent be emailed John W. Slater at the
NASA John H. Glenn Research Center.

Last Updated: Wednesday, 02-Jul-2008 13:52:24 EDT

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