Similarly shaped airfoils to NACA35009
New! Bulk download of polars in Excel format: NACA35009.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. NACA45009
3. Fage & Collins 2
4. HS 3.0/9.0
5. NACA63-509 a=0.2
6. Ritz 3-30-10
7. NACA34009
8. NACA63-509 a=0.0
9. NACA35010
10. NACA64-509 a=0.2
11. NACA44010
12. NACA64-509 a=0.0
13. NACA45010
14. NACA63-609 a=0.0
15. Horten 9.00% thick 4.00% camber
16. NACA63-510 a=0.2
17. NACA64-609 a=0.0
18. NACA63-610 a=0.0
19. NACA64-510 a=0.2
20. NACA65-509 a=0.2
21. NACA63-510 a=0.0