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
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. NACA63A610
3. GOE 547
4. SG6042
5. NACA64A610
6. FX 83-W-108
7. NACA63-610 a=0.8
8. EPPLER 66
9. NACA64-610 a=0.8
10. NACA63-611 a=0.8
11. NACA64-611 a=0.8
12. GOE 546
13. NACA63-710
14. GOE 602 MOD.
15. NACA64-710
16. NACA63A611
17. NACA63-711
18. NACA64-711
19. NACA65-610 a=0.8
20. PSU 94-097 (AIAA 2001-2478)
21. HQ 3.5/10