Similarly shaped airfoils to BOEING-VERTOL VR-7
New! Bulk download of polars in Excel format: vr7.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (19) | 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
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2. Ritz 3-30-12
3. NACA63-512 a=0.2
4. NACA63-612 a=0.0
5. BOEING-VERTOL VR-5
6. NACA64-512 a=0.2
7. NACA64-612 a=0.0
8. USA 45 M
9. NACA63-512 a=0.0
10. EPPLER 195
11. NACA63-613 a=0.0
12. NACA64-512 a=0.0
13. NACA63-612 a=0.2
14. GA 35-412
15. NACA63-513 a=0.2
16. MS3-11Retro
17. GA 35A412
18. GA 37-412
19. NACA64-613 a=0.0
20. NACA64-612 a=0.2
21. MH 70 11.08%