Similarly shaped airfoils to DEFIANT CANARD BL20
New! Bulk download of polars in Excel format: defcnd1.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. GA 30-620
3. GA 35-620
4. GA 30-619
5. NACA63-720 a=0.5
6. GOE 735
7. GA 30A620
8. GA 30A619
9. NACA63-720 a=0.6
10. GOE 383
11. NACA63-620 a=0.5
12. NACA63-720 a=0.2
13. GA 37-620
14. NACA64-720 a=0.5
15. GA 35A620
16. NACA63-620 a=0.6
17. GA 35-619
18. GOE 424
19. NACA63-719 a=0.5
20. GA 30U-618
21. GA 30-618