Similarly shaped airfoils to DAVIS BASIC B-24 WING
New! Bulk download of polars in Excel format: davis_corrected.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. SSV2316 VANS RV-10
3. GOE 738
4. NACA63-516 a=0.0
5. NACA63-416 a=0.0
6. NACA64-416 a=0.2
7. NACA35015
8. MH 104 15.28%
9. NACA63-415 a=0.2
10. NACA64-516 a=0.0
11. NACA63-417 a=0.2
12. GA 30-215
13. NACA64-416 a=0.0
14. NACA63-415 a=0.0
15. NACA63-516 a=0.2
16. GA 30-315
17. NACA63-517 a=0.0
18. NACA35016
19. NACA63-515 a=0.0
20. NACA2215
21. ATR72SM