Similarly shaped airfoils to NACA66A315
New! Bulk download of polars in Excel format: NACA66A315.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. NACA66-415
3. NACA66-315 a=0.6
4. NACA66-315
5. NACA66-315 a=0.5
6. NACA65A315
7. NACA66-316 a=0.8
8. NACA66A316
9. NACA66A314
10. NACA66-314 a=0.8
11. NACA66-416
12. NACA65A316
13. NACA66-316 a=0.6
14. NACA 66,2-(1.8)15.5 A=.6 P-51 ROOT
15. NACA66-314 a=0.6
16. NACA66-414
17. NACA66(2)-415
18. NACA66-314
19. NACA66-215 a=0.6
20. NACA66-215 a=0.8
21. NACA67A314