Similarly shaped airfoils to NACA63-311
New! Bulk download of polars in Excel format: NACA63-311.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 1.5/11
3. NACA63-211 a=0.8
4. NACA63-211 a=0.6
5. NACA64-211 a=0.8
6. NACA63-311 a=0.8
7. NACA64-211 a=0.6
8. GA 35-211
9. GA 37-211
10. TPR-95-96-95
11. NACA64-311 a=0.8
12. NACA63-211 a=0.5
13. EM CY 1016 1510
14. NACA64-211 a=0.5
15. HQ 1.5/10
16. TP210-11%
17. NACA65-311
18. NACA63-312
19. HN-980
20. NACA63-310
21. NACA63A311