Similarly shaped airfoils to NACA63-309 a=0.0
New! Bulk download of polars in Excel format: NACA63-309%20a%3D0.0.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. NACA63-309 a=0.2
3. NACA64-309 a=0.2
4. MH 42 8.94%
5. MH 20 9.01%
6. NACA65-309 a=0.0
7. MH 43 8.5%
8. NACA63-209 a=0.5
9. NACA65-309 a=0.2
10. DD928416
11. NACA64-209 a=0.5
12. MH 46 9.1%
13. NACA2209
14. RG 14
15. NACA63-209 a=0.6
16. NACA M11
17. GIII BL387
18. NACA64-209 a=0.6
19. MH 62 9.3%
20. KC-135 BL351.6
21. BOEING 707 .54 SPAN