Similarly shaped airfoils to HSNLF(1)-0213
New! Bulk download of polars in Excel format: hsnlf213.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. NACA65-214 a=0.2
3. NACA65-214 a=0.5
4. NACA65-213 a=0.2
5. NACA65-313 a=0.0
6. NACA66-213 a=0.2
7. NACA65-214 a=0.0
8. NACA66-313 a=0.0
9. NACA65-214 a=0.6
10. NACA65-314 a=0.2
11. NACA65-213 a=0.5
12. NACA66-213 a=0.5
13. NACA65-213 a=0.0
14. NACA66-213 a=0.0
15. NACA65-213 a=0.6
16. NACA66-213 a=0.6
17. NACA65-313 a=0.2
18. NACA66-313 a=0.2
19. NACA65-214 a=0.8
20. NACA65A213
21. NACA64-314 a=0.0