Similarly shaped airfoils to NACA M14 (NACA-TR-221)
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 M17 (NACA-TR-221)
3. Fage & Collins 2
4. Eiffel 428 (Bleriot)
5. NACA64-609 a=0.0
6. NACA65-609 a=0.0
7. NACA63-609 a=0.0
8. I.S.A. 571
9. NACA45009
10. HL75-K-3
11. NACA64-509 a=0.2
12. NACA65-509 a=0.2
13. NACA63-509 a=0.2
14. NACA64-609 a=0.2
15. NACA35009
16. NACA63-609 a=0.2
17. NACA65-609 a=0.2
18. NACA M14
19. Fage & Collins 1
20. NACA66-609 a=0.0
21. NACA64-509 a=0.0