Similarly shaped airfoils to EPPLER 715
New! Bulk download of polars in Excel format: e715.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. GA 35-314
3. NACA63-414 a=0.5
4. NACA63-414 a=0.6
5. GA 35-315
6. NACA63-415 a=0.5
7. EPPLER 197
8. MID 393 UL
9. NACA63-415 a=0.6
10. MS2.5/13GPV
11. MS2.5/15GPV
12. NACA63-514 a=0.2
13. Joukowsky 15.00% thick 3.00% camber
14. NACA63-514 a=0.0
15. Joukowsky 14.00% thick 3.00% camber
16. GA 37-314
17. NACA63-414 a=0.8
18. EPPLER 209
19. NACA63-515 a=0.2
20. EPPLER 203
21. NACA63-514