Similarly shaped airfoils to NACA66A213
New! Bulk download of polars in Excel format: NACA66A213.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. NACA66-213 a=0.6
3. NACA66-213
4. NACA66-213 a=0.5
5. NACA66-313
6. NACA65A213
7. NACA66-213 a=0.2
8. NACA66-213 a=0.0
9. NACA66-214 a=0.8
10. NACA66A214
11. NACA66A212
12. NACA66-212 a=0.8
13. NACA66(1)-212
14. NACA67-213 a=0.8
15. NACA67A213
16. NACA66-214 a=0.6
17. NACA 66,2-(1.8)12 A=.6 P-51 TIP
18. NACA65A214
19. NACA66-212 a=0.6
20. NACA66-212
21. NACA67A212