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Subsonic turbulent flow past two element NLR-7301 configuration

In this study, computations are performed for steady, subsonic and turbulent flow past two element NLR-7301 configuration. NLR-7301 configuration consists of a main element and a flap. The gap between these elements is 2.6% of the main element chord. The configuration is designed with moderate flap angle of 20 degrees.

Grid Details

Grid
Mach fill plot
S.No
Grid Type
Elements
No of cells (Mn)
1
Unstructured Hybrid
Quadrilaterals
16,298
2
Unstructured Hybrid
Triangles
16,298

Test Conditions

Altitude
Angle of Attack (°)
Mach Number (°)
Reynolds Number (Mn/Mtr)
-
13.1°
0.185
2.51e06

Results

Mach plots

Flow separation can be seen on the upper surface of main element as well as at the trailing edge of the flap.

Main Element - Grid
Main Element - Mach fill plot
Main Element - Streamlines
Flap - Grid
Flap - Mach fill plot
Flap - Streamlines
Average Y+

Average Y+ on the surfaces of airfoil and flap is less than one. This ensures that the skin friction is well captured. Surface pressure and skin friction distributions agree well with the experimental results.

CP Distribution
CF Distribution

References

van der Berg B.,``Boundary layer measurements on a two dimensional wing with flap", Report Number NLR TR-79009 U, Dutch Aerospace Laboratory(NLR), 1979.

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