Similarly shaped airfoils to GA 35-315
New! Bulk download of polars in Excel format: GA%2035-315.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. NACA63-415 a=0.5
3. NACA63-415 a=0.6
4. NACA64-415 a=0.5
5. NACA64-415 a=0.6
6. NACA63-415 a=0.8
7. NACA63-515
8. MS2.5/15GPV
9. S2027
10. NACA64-415 a=0.8
11. NACA64-515
12. GA 35-316
13. GA 35-314
14. NACA64(2)-415
15. NACA63-414 a=0.5
16. GA 35A315
17. GA 37-314
18. NACA63-515 a=0.0
19. NACA63-414 a=0.6
20. NACA63-416 a=0.5
21. GA 37-316