Similarly shaped airfoils to NACA M14
New! Bulk download of polars in Excel format: m14.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
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2. NACA64-609 a=0.2
3. GOE 490
4. NACA65-609 a=0.2
5. GOE 408
6. NACA63-609 a=0.2
7. NACA M17
8. GOE 315 (HANSA-BRANDENBURG III.5)
9. NACA64-709 a=0.0
10. NACA65-709 a=0.0
11. NACA63-709 a=0.0
12. AQUILA 9.3% smoothed
13. GOE 585
14. GOE 328
15. GOE 316 (HANSA-BRANDENBURG IV.5)
16. NACA65-609 a=0.0
17. NACA64-609 a=0.0
18. GOE 286
19. NACA66-609 a=0.2
20. NACA64-509 a=0.5
21. NACA65-509 a=0.5