Similarly shaped airfoils to NACA63-709 a=0.5
New! Bulk download of polars in Excel format: NACA63-709%20a%3D0.5.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. NACA63-709 a=0.6
3. NACA64-709 a=0.6
4. NACA65-709 a=0.5
5. NACA63-710 a=0.5
6. NACA65-709 a=0.6
7. NACA64-710 a=0.5
8. NACA63-710 a=0.6
9. NACA64-710 a=0.6
10. GA 35-610
11. GA 37-610
12. GOE 287
13. S4320
14. NACA65-710 a=0.5
15. GOE 326 (PFALZ 55)
16. GOE 117 (MVA MK.4)
17. NACA63-609 a=0.5
18. NACA64-609 a=0.5
19. NACA63-609 a=0.6
20. NACA64-609 a=0.6
21. GOE 610 B