Swallow P-30
New! Bulk download of polars in Excel format: SwallowP-30.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (0) | 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):
Swallow P-30
1.00000000 0.00000000
0.90000000 -0.00050000
0.80000000 0.00200000
0.70000000 0.01100000
0.60000000 0.02400000
0.50000000 0.03800000
0.40000000 0.05000000
0.30000000 0.06000000
0.20000000 0.06150000
0.10000000 0.04900000
0.05000000 0.03938000
0.02000000 0.02075000
0.00000000 0.00000000
0.00000000 0.00000000
0.02000000 -0.00800000
0.05000000 -0.00700000
0.10000000 -0.00100000
0.20000000 0.00000000
0.30000000 -0.00300000
0.40000000 -0.01000000
0.50000000 -0.01800000
0.60000000 -0.02600000
0.70000000 -0.02800000
0.80000000 -0.02800000
0.90000000 -0.01900000
1.00000000 0.00000000