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Subsonic turbulent flow past MDA four element airfoil configuration

In this study, computations are performed for steady, subsonic and turbulent flow past four element MDA configuration. This configuration consists of a slat, a main element, a primary flap and an auxiliary flap as shown in figure below.

Grid Details

Grid
S.No
Grid Type
Elements
No of cells (Mn)
1
Unstructured
Quadrilaterals
1,27,173
2
Unstructured
Triangles
1,27,173

Test Conditions

Altitude
Angle of Attack (°)
Mach Number (°)
Reynolds Number (Mn/Mtr)
-
18.0°
0.2
9.0e06

Results

Mach Plots (Slat)

A separation bubble can be seen in the coves of "Slat".

Grid
Mach Fill Plot
Streamlines
Mach Plots (Main Element)

A separation bubble can be seen in the coves of "Main Element".

Grid
Mach fill plot
Streamlines
Mach Plots (Main Flap)

A separation bubble can be seen in the coves of "Primary Flap".

Grid
Mach fill plot
Streamlines
Mach Plots (Auxillary Flap)

A separation bubble can be seen in the coves of "Primary Flap".

Grid
Mach fill plot
Streamlines
Cl-Alpha & Cd-Alpha curves:

An excellent comparison of computed lift and drag coefficients is seen with the experimental results till the stall angle.

Cl vs Alpha
Cd vs Alpha

References

Daryl L. Bonhaus, W. Kyle Anderson and Dimitri J. Mavriplis, ``Numerical study to assess Sulfur Hexafluoride as a medium for testing multi element aerofoils", NASA Technical Paper 3496, June 1995.

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