Similarly shaped airfoils to GA 35-019
New! Bulk download of polars in Excel format: GA%2035-019.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. NACA63-119 a=0.0
3. NACA64-119 a=0.0
4. NACA63-119
5. NACA64-119
6. NACA63-119 a=0.2
7. NACA64-119 a=0.2
8. GA 35-018
9. GA 35-020
10. NACA63(3)-018
11. NACA63-018
12. NACA63-119 a=0.8
13. GA 37-018
14. NACA63-119 a=0.5
15. NACA64-119 a=0.8
16. NACA63-119 a=0.6
17. NACA64-119 a=0.5
18. NACA64-018
19. NACA64-119 a=0.6
20. NACA63-120 a=0.0
21. GA 37-020