Similarly shaped airfoils to GA 37-320
New! Bulk download of polars in Excel format: GA%2037-320.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
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. NACA64-420 a=0.6
3. NACA64-420 a=0.5
4. NACA64-520
5. GA 37-319
6. NACA63-420 a=0.6
7. NACA63-420 a=0.5
8. NACA64-420 a=0.8
9. GA 35A319
10. GA 35A320
11. NACA64-620
12. NACA64-520 a=0.5
13. GA 35-319
14. NACA64-520 a=0.6
15. NACA63-520
16. GA 40-320
17. NACA65-420 a=0.6
18. NACA65-420 a=0.5
19. NACA64-520 a=0.8
20. NACA63-420 a=0.8
21. GA 40A320