Similarly shaped airfoils to NACA 5-H-15
New! Bulk download of polars in Excel format: n5h15.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. NACA 747A315
3. NACA65-516 a=0.0
4. TsAGI B 15.0% thick
5. NACA65-416 a=0.2
6. TsAGI B 15.5% thick
7. TsAGI B 14.5% thick
8. NACA65-515 a=0.0
9. NACA 747A415
10. NACA65-516 a=0.2
11. NACA65-415 a=0.2
12. NACA65-416 a=0.0
13. EPPLER 642
14. NACA64-516 a=0.0
15. NACA65-415 a=0.0
16. NACA66-515 a=0.0
17. NACA65-515 a=0.2
18. NACA66-415 a=0.2
19. TsAGI B 16.0% thick
20. TsAGI B 14.0% thick
21. NACA64-516 a=0.2