CLARK YH
New! Bulk download of polars in Excel format: clarkyh.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (33) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
DXF file of spline and points: download
Lednicer-format DAT file download
VisualFoil-format DAT file download
X,Y,Z CSV file download
Selig-format DAT file (download):
CLARK YH AIRFOIL
1.00000000 -0.02000000
0.95000000 -0.01250000
0.90000000 -0.00400000
0.80000000 0.01500000
0.70000000 0.03450000
0.60000000 0.05000000
0.50000000 0.06400000
0.40000000 0.07350000
0.30000000 0.07800000
0.20000000 0.07200000
0.15000000 0.06700000
0.10000000 0.05700000
0.07500000 0.04900000
0.05000000 0.04000000
0.02500000 0.02700000
0.00000000 0.00000000
0.00000000 0.00000000
0.02500000 -0.02250000
0.05000000 -0.02900000
0.07500000 -0.03400000
0.10000000 -0.03650000
0.15000000 -0.04100000
0.20000000 -0.04100000
0.30000000 -0.04100000
0.40000000 -0.04100000
0.50000000 -0.04100000
0.60000000 -0.04100000
0.70000000 -0.04100000
0.80000000 -0.03700000
0.90000000 -0.03100000
0.95000000 -0.02730000
1.00000000 -0.02100000