Similarly shaped airfoils to GIII BL75
New! Bulk download of polars in Excel format: giiic.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
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2. GIII BL45
3. HAWKER TEMPEST 96.77% SEMISPAN
4. NACA65-110 a=0.2
5. NACA65-110 a=0.0
6. NACA65-110 a=0.5
7. RC10-64C
8. Horten 10.00% thick 1.00% camber
9. NACA64A110
10. NACA63A110
11. NACA65-210 a=0.0
12. NACA65-110 a=0.6
13. NACA65A110
14. NACA65-111 a=0.2
15. NACA22010
16. NACA65-111 a=0.0
17. NACA65-111 a=0.5
18. NACA64-111 a=0.2
19. NACA65-211 a=0.0
20. NACA64-110 a=0.2
21. NACA66-110 a=0.2