Similarly shaped airfoils to GA 37-319
New! Bulk download of polars in Excel format: GA%2037-319.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. NACA64-419 a=0.6
3. NACA64-419 a=0.5
4. NACA63-419 a=0.6
5. NACA63-419 a=0.5
6. NACA64-519
7. GA 37-318
8. GA 37-320
9. NACA64-419 a=0.8
10. GA 35A319
11. GA 35A318
12. GA 35-320
13. NACA63-519
14. GA 40-319
15. GA 35-318
16. NACA64-519 a=0.5
17. NACA64-420 a=0.6
18. NACA65-419 a=0.6
19. NACA63-419 a=0.8
20. NACA64-619
21. NACA65-419 a=0.5