Similarly shaped airfoils to DEFIANT CANARD BL110
New! Bulk download of polars in Excel format: defcnd2.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. MID 321d
3. AH 93-W-145
4. GOE 632
5. AH 83-150 Q
6. NACA64-715 a=0.2
7. NACA64-715 a=0.0
8. Eiffel 371 (Monge)
9. CLARK YM-15
10. NACA63-715 a=0.0
11. NACA63-715 a=0.2
12. NACA65-715 a=0.0
13. MRC-16
14. NACA64-615 a=0.2
15. GA 35A415
16. DU 99-146
17. NACA65-615 a=0.2
18. NACA63-615 a=0.2
19. NACA4315
20. FX 84-W-150
21. NACA64-716 a=0.2