Similarly shaped airfoils to NACA63-709 a=0.2
New! Bulk download of polars in Excel format: NACA63-709%20a%3D0.2.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. NACA63-709 a=0.0
3. NACA64-709 a=0.0
4. NACA65-709 a=0.2
5. NACA63-710 a=0.2
6. NACA65-709 a=0.0
7. GOE 316 (HANSA-BRANDENBURG IV.5)
8. NACA64-710 a=0.2
9. GOE 318 (HANSA-BRANDENBURG VI.5)
10. AQUILA 9.3% smoothed
11. GOE 287
12. NACA63-609 a=0.5
13. NACA63-609 a=0.2
14. NACA64-609 a=0.2
15. GOE 315 (HANSA-BRANDENBURG III.5)
16. GOE 188
17. NACA63-710 a=0.0
18. NACA64-609 a=0.5
19. NACA64-710 a=0.0
20. GOE 277 (DAIMLER VIII)
21. GOE 328