Similarly shaped airfoils to EPPLER 642
New! Bulk download of polars in Excel format: e642.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. NACA65-516 a=0.2
3. NACA65-515 a=0.2
4. RONCZ 1082T VOYAGER TIP OUTER AFT WING
5. EPPLER 682
6. NACA65-515 a=0.0
7. AH 79-K-143/18
8. NACA65-516 a=0.0
9. NACA65-616 a=0.0
10. NACA66-515 a=0.2
11. MB253515 15.0% smoothed
12. GA 40A316
13. NACA65-615 a=0.0
14. GA 37A315
15. GA 40-316
16. FX 79-K-144/17
17. NACA65-416 a=0.5
18. NACA65-415 a=0.5
19. GA 40A315
20. NACA65(2)-415 a=0.5
21. GA 37A316