Similarly shaped airfoils to GIII BL45
New! Bulk download of polars in Excel format: giiib.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
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2. GIII BL0
3. NACA65-111 a=0.2
4. NACA65-111 a=0.0
5. GIII BL86
6. NACA22010.5
7. NACA64A111
8. NPL 9660
9. NPL 9615
10. NACA63A111
11. NACA65-111 a=0.5
12. Horten 11.00% thick 1.00% camber
13. NACA64-111 a=0.2
14. NACA65-111 a=0.6
15. NACA64-111 a=0.0
16. RC10-64C
17. NACA65A111
18. NACA22110.5
19. NACA65-111
20. HAWKER TEMPEST 96.77% SEMISPAN
21. NACA65-111 a=0.8