Similarly shaped airfoils to NACA64A215
New! Bulk download of polars in Excel format: NACA64A215.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (66) | 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. NACA65-215 a=0.8
3. NACA65(2)-215
4. NACA65-215 a=0.6
5. NACA65-215
6. NACA65-215 a=0.5
7. NACA65A215
8. NACA65-315
9. NACA64-215 a=0.8
10. NACA64A216
11. NACA64A214
12. NACA65-215 a=0.2
13. NACA64(2)-215
14. HAWKER TEMPEST 37.5% SEMISPAN
15. NACA63A214
16. NACA64-215 a=0.6
17. NACA65-216 a=0.8
18. NACA64-215
19. NACA65A214
20. NACA64-215 a=0.5
21. NACA63A216