Similarly shaped airfoils to RAF 32 MOD


New! Bulk download of polars in Excel format: raf32md.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
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.

1. MH 116 9.84%
2. NACA63A610
3. GOE 547
4. SG6041_PSO
5. SG6042
6. NACA64A610
7. FX 83-W-108
8. NACA63-610 a=0.8
9. EPPLER 66
10. NACA64-610 a=0.8
11. NACA63-611 a=0.8
12. NACA64-611 a=0.8
13. GOE 546
14. NACA63-710
15. GOE 602 MOD.
16. NACA64-710
17. NACA63A611
18. NACA63-711
19. NACA64-711
20. NACA65-610 a=0.8
21. PSU 94-097 (AIAA 2001-2478)