Similarly shaped airfoils to NACA64-709 a=0.2
New! Bulk download of polars in Excel format: NACA64-709%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
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. NACA65-709 a=0.2
3. NACA64-709 a=0.0
4. NACA63-709 a=0.0
5. NACA65-709 a=0.0
6. NACA64-710 a=0.2
7. NACA63-710 a=0.2
8. GOE 316 (HANSA-BRANDENBURG IV.5)
9. AQUILA 9.3% smoothed
10. GOE 287
11. GOE 318 (HANSA-BRANDENBURG VI.5)
12. GOE 188
13. NACA65-710 a=0.2
14. NACA64-609 a=0.5
15. NACA64-609 a=0.2
16. NACA64-710 a=0.0
17. NACA63-609 a=0.5
18. NACA63-609 a=0.2
19. NACA63-710 a=0.0
20. NACA66-709 a=0.2
21. NACA65-609 a=0.2