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
Dynamic plotter New!
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.
1. GIII BL75
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