Similarly shaped airfoils to NACA65A212
New! Bulk download of polars in Excel format: NACA65A212.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (2) | 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. NACA66A212
3. NACA66-212 a=0.8
4. NACA65-212 a=0.8
5. NACA66(1)-212
6. NACA 66,2-(1.8)12 A=.6 P-51 TIP
7. NACA65(1)-212
8. NACA66-212 a=0.6
9. NACA65-212 a=0.6
10. NACA66-212
11. NACA66-212 a=0.5
12. NACA65-212
13. NACA65-212 a=0.5
14. NACA65(1)-212 a=0.6
15. NACA63A212
16. LOCKHEED C-141 BL426.57
17. LOCKHEED C-5A BL488.2
18. NACA66-312
19. NACA65-312
20. NACA65-213 a=0.8
21. LOCKHEED C-5A BL758.6