Similarly shaped airfoils to EPPLER 502
New! Bulk download of polars in Excel format: e502.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.
2. NACA66-315 a=0.0
3. NACA65-316 a=0.2
4. NACA66-315 a=0.2
5. NACA66-316 a=0.0
6. NACA65-216 a=0.5
7. NACA 66,2-(1.8)15.5 A=.6 P-51 ROOT
8. NACA66-215 a=0.5
9. NACA66-316 a=0.2
10. NACA65-216 a=0.2
11. NACA66-215 a=0.2
12. NACA65-216 a=0.6
13. NACA66-215 a=0.6
14. NACA66-216 a=0.5
15. GA 40A216
16. NACA66-216 a=0.2
17. NACA66-216 a=0.6
18. GA 40-216
19. NACA65A216
20. NACA65-315 a=0.0
21. NACA66-215 a=0.0