Similarly shaped airfoils to NACA 5-H-20
New! Bulk download of polars in Excel format: n5h20.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
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.
2. NACA66-720 a=0.2
3. NACA66-719 a=0.2
4. NACA65-720 a=0.0
5. NACA66-720 a=0.0
6. NACA66-719 a=0.0
7. NACA65-719 a=0.2
8. NACA65-620 a=0.2
9. NACA66-620 a=0.2
10. NACA65-719 a=0.0
11. NACA66-619 a=0.2
12. NACA66-718 a=0.2
13. NACA64-720 a=0.2
14. NACA66-718 a=0.0
15. NACA65-619 a=0.2
16. NACA65-620 a=0.0
17. TsAGI B 20.0% thick
18. NACA65-620 a=0.5
19. TsAGI B 19.5% thick
20. NACA66-620 a=0.5
21. NACA67-719 a=0.2