Similarly shaped airfoils to NACA 11-H-09
New! Bulk download of polars in Excel format: n11h9.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. NACA M17
3. NACA64-709 a=0.0
4. GOE 746
5. NACA63-709 a=0.0
6. NACA45109
7. NACA65-709 a=0.0
8. GOE 318 (HANSA-BRANDENBURG VI.5)
9. NACA64-709 a=0.2
10. NACA63-709 a=0.2
11. NACA64-609 a=0.2
12. NACA64-710 a=0.0
13. NACA63-609 a=0.2
14. NACA63-710 a=0.0
15. NACA45009
16. NACA65-609 a=0.2
17. NACA65-709 a=0.2
18. GOE 316 (HANSA-BRANDENBURG IV.5)
19. Horten 9.00% thick 5.00% camber
20. NACA64-710 a=0.2
21. NACA63-710 a=0.2