Similarly shaped airfoils to NACA63-309
New! Bulk download of polars in Excel format: NACA63-309.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. HQ 1.5/9 B
3. HQ 1.5/9
4. HQ 1.5/8.5
5. TP202-9%
6. HN-163TA
7. NACA63-209 a=0.8
8. HN-436
9. HN-1054
10. NACA64-209 a=0.8
11. HN-1015
12. NACA63-209 a=0.6
13. NACA64-209 a=0.6
14. NACA65-309
15. NACA63-309 a=0.8
16. S2050 8.93%
17. HN-184
18. HS 1.7/9
19. NACA64-309 a=0.8
20. TP-CIEL-S
21. NACA63-209 a=0.5