Similarly shaped airfoils to NACA65-210 a=0.0
New! Bulk download of polars in Excel format: NACA65-210%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
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. NACA64-210 a=0.0
3. NACA64-210 a=0.2
4. NACA65-210 a=0.5
5. NACA65-210
6. NACA65-210 a=0.6
7. NACA63-210 a=0.0
8. GIII BL86
9. KC-135 BL200.76
10. NACA63-210 a=0.2
11. NACA64-210 a=0.5
12. RC-10(N)1
13. NACA65-210 a=0.8
14. NACA65-110 a=0.5
15. NACA66-210 a=0.0
16. NACA64-210
17. BOEING 737 MIDSPAN
18. NACA65-110 a=0.6
19. NACA64A210
20. NACA66-210 a=0.2
21. SIKORSKY SSC-A09