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Subsonic turbulent flow past three element NHLP2D configuration

In this study, computations are performed for steady, subsonic and turbulent flow past three element NHLP configuration. NHLP configuration consists of a slat, a main element and a flap as shown in figure below.

Grid Details

Grid
Mach fill plot
S.No
Grid Type
Elements
No of cells (Mn)
1
Structured
Quadrilaterals
2,64,011

Test Conditions

Altitude
Angle of Attack (°)
Mach Number (°)
Reynolds Number (Mn/Mtr)
-
21.0°
0.197
3.52e06

Results

Mach plots

Flow separation can be seen on the upper surface of main element. A complex flow involving multiple shear layers emanating from slat and main element are seen in the region around flap.

Slat - Grid
Slat- Mach fill plot
Slat - Streamlines
Main Element - Grid
Main Element - Grid
Main Element - Mach fill plot
Flap - Grid
Flap - Mach fill plot
Flap - Streamlines
Cl-Alpha & Cd-Alpha Curves

Till angle of attack equal to 20 degrees, lift and drag coefficients obtained using HiFUN compare well with the experimental values.

Cl vs Alpha
Cd vs Alpha

References

CL Rumsey, SX Ying, ``Prediction of high lift: Review of present CFD capability", Progress in Aerospace Sciences, 2002 - Elsevier.
M Murayama, K Yamamoto, K Kobayashi, ``Validation of Flows on High-Lift Configurations by Structured- and Unstructured- Mesh Method", AIAA Paper, 2005.
Fejtek I.,``Summary of code validation results for a multielement aerofoil test case", AIAA paper 97-1932, June-July 1997.

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