Similarly shaped airfoils to RAF 33
New! Bulk download of polars in Excel format: raf33.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
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. EPPLER 638
3. NACA63-713 a=0.2
4. NACA64-713 a=0.2
5. EPPLER 639
6. NACA63-713 a=0.0
7. FX 05-H-126
8. NACA64-713 a=0.0
9. AH 80-140
10. NACA63-714 a=0.2
11. NACA64-714 a=0.2
12. EPPLER 334
13. NACA65-713 a=0.2
14. NACA M15
15. NACA63-714 a=0.0
16. NACA65-713 a=0.0
17. FX 77-W-121
18. NACA64-714 a=0.0
19. NACA63-712 a=0.2
20. NACA45112
21. GOE 633