Similarly shaped airfoils to BOEING-VERTOL VR-7 WITH TAB
New! Bulk download of polars in Excel format: vr7b.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. NACA63-512 a=0.2
3. NACA63-612 a=0.0
4. BOEING-VERTOL VR-5
5. NACA64-512 a=0.2
6. NACA64-612 a=0.0
7. Ritz 3-30-12
8. USA 45 M
9. NACA63-512 a=0.0
10. NACA63-613 a=0.0
11. NACA63-612 a=0.2
12. GA 35-412
13. NACA64-512 a=0.0
14. NACA63-513 a=0.2
15. EPPLER 195
16. GA 37-412
17. MH 70 11.08%
18. NACA64-612 a=0.2
19. NACA64-613 a=0.0
20. NACA63-511 a=0.2
21. NACA63-512 a=0.5