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
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. NACA45009
4. NACA65-609 a=0.2
5. NACA63-609 a=0.2
6. NACA64-609 a=0.0
7. NACA65-609 a=0.0
8. NACA63-609 a=0.0
9. NACA64-709 a=0.0
10. NACA63-709 a=0.0
11. Fage & Collins 2
12. NACA65-709 a=0.0
13. NACA 11-H-09
14. GOE 315 (HANSA-BRANDENBURG III.5)
15. NACA66-609 a=0.2
16. Eiffel 428 (Bleriot)
17. I.S.A. 571
18. NACA66-609 a=0.0
19. GOE 318 (HANSA-BRANDENBURG VI.5)
20. NACA35009
21. GOE 309 (MVA H.41)