Similarly shaped airfoils to NACA65-309 a=0.0
New! Bulk download of polars in Excel format: NACA65-309%20a%3D0.0.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
Dynamic plotter New!
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. BOEING 707 .54 SPAN
3. KC-135 BL351.6
4. NACA64-309 a=0.0
5. NACA64-309 a=0.2
6. BOEING 707 .99 SPAN
7. NACA63-309 a=0.0
8. NACA63-309 a=0.2
9. NACA65-209 a=0.5
10. NACA66-309 a=0.0
11. NACA66-309 a=0.2
12. DP1.68/8.37_DS
13. NACA65-209 a=0.6
14. GIII BL369
15. NACA M11
16. NACA65-209 a=0.2
17. DP1.87/9.07_DS
18. GIII BL332
19. GIII BL387
20. NACA64-209 a=0.5
21. NACA64-310 a=0.0