Similarly shaped airfoils to NACA M17
New! Bulk download of polars in Excel format: m17.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
Dynamic plotter New!
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. NACA M14 (NACA-TR-221)
3. NACA M14
4. NACA64-609 a=0.2
5. NACA45009
6. NACA65-609 a=0.2
7. NACA63-609 a=0.2
8. NACA64-609 a=0.0
9. NACA65-609 a=0.0
10. NACA63-609 a=0.0
11. NACA64-709 a=0.0
12. NACA63-709 a=0.0
13. Fage & Collins 2
14. NACA65-709 a=0.0
15. NACA 11-H-09
16. GOE 315 (HANSA-BRANDENBURG III.5)
17. NACA66-609 a=0.2
18. Eiffel 428 (Bleriot)
19. I.S.A. 571
20. NACA66-609 a=0.0
21. GOE 318 (HANSA-BRANDENBURG VI.5)