Similarly shaped airfoils to NACA M18
New! Bulk download of polars in Excel format: m18.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (8) | 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 M15
3. NACA M15 (NACA-TR-221)
4. EPPLER 334
5. RAF 33
6. NACA64-713 a=0.0
7. NACA65-713 a=0.0
8. NACA65-613 a=0.2
9. NACA65-712 a=0.0
10. NACA65-612 a=0.2
11. NACA64-613 a=0.2
12. NACA63-713 a=0.0
13. NACA45012
14. NACA4312
15. NACA64-713 a=0.2
16. NACA64-712 a=0.0
17. NACA63-613 a=0.2
18. EPPLER 638
19. NACA65-713 a=0.2
20. NACA64-612 a=0.2
21. GOE 285