Similarly shaped airfoils to NACA65-412 a=0.8
New! Bulk download of polars in Excel format: NACA65-412%20a%3D0.8.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
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2. NACA64A412
3. NACA65(1)-412
4. NACA63A412
5. NACA65-412 a=0.6
6. NACA65A412
7. NACA64-412 a=0.8
8. NACA64-512
9. GA 40-312
10. GA 40A312
11. HL74-351
12. NACA65-412 a=0.5
13. NACA64-412 a=0.6
14. NACA65A411
15. NACA65-413 a=0.8
16. NACA65-411 a=0.8
17. GA 37A312
18. NACA65-412
19. HL743512
20. NACA63-412 a=0.8
21. NACA64A411