Similarly shaped airfoils to M-451-12.0
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
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. AH 80-136
3. NACA64-612 a=0.0
4. NACA63-612 a=0.0
5. EPPLER 637
6. NACA64-512 a=0.2
7. NACA63-512 a=0.2
8. NACA64-613 a=0.0
9. NACA65-612 a=0.0
10. HS 3.4.12b
11. NACA63-613 a=0.0
12. NACA64-612 a=0.2
13. NACA63-612 a=0.2
14. NACA45012
15. HS 3.5/12
16. FX 05-H-126
17. NACA65-512 a=0.2
18. M-35A-12.7
19. NACA64-512 a=0.0
20. NACA35112
21. NACA63-512 a=0.0