Similarly shaped airfoils to GA 40A320
New! Bulk download of polars in Excel format: GA%2040A320.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. GA 37A320
3. NACA65-420 a=0.6
4. NACA65-420 a=0.5
5. NACA65-520
6. NACA65-420 a=0.8
7. GA 35A320
8. GA 40A319
9. NACA65(421)-420
10. GA 40-319
11. GA 37A319
12. NACA65-421 a=0.5
13. NACA64A420
14. NACA65-520 a=0.2
15. GA 37-320
16. NACA65-520 a=0.5
17. NACA65-419 a=0.5
18. NACA65-419 a=0.6
19. NACA65-620
20. GA 35A319
21. NACA65-520 a=0.0