Similarly shaped airfoils to BOEING-VERTOL VR-5
New! Bulk download of polars in Excel format: vr5.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. NACA64-612 a=0.2
3. NACA63-612 a=0.0
4. NACA63-612 a=0.2
5. BOEING-VERTOL VR-7 WITH TAB
6. BOEING-VERTOL VR-7
7. NACA65-612 a=0.0
8. NACA64-512 a=0.2
9. NACA65-612 a=0.2
10. GA 37-412
11. NACA64-512 a=0.5
12. NACA63-512 a=0.2
13. NACA63-512 a=0.5
14. GA 35-412
15. NACA64-712 a=0.0
16. NACA64-613 a=0.2
17. GA 35A412
18. NACA65-512 a=0.2
19. NACA64-613 a=0.0
20. NACA63-712 a=0.0
21. GA 40-412