Similarly shaped airfoils to NACA 5-H-10
New! Bulk download of polars in Excel format: n5h10.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. NACA65-310 a=0.2
3. RC(5)-10
4. NACA65-410 a=0.0
5. NACA65-310 a=0.0
6. NACA66-310 a=0.2
7. NACA64-310 a=0.2
8. NACA66-310 a=0.0
9. NACA64-410 a=0.0
10. NACA66-410 a=0.0
11. B-29 TIP
12. NACA64-310 a=0.0
13. RC_Milan
14. Sipkill 1.7/10
15. BOEING-VERTOL VR-13
16. RC-10(N)1
17. TsAGI B 10.0% thick
18. NACA65-311 a=0.2
19. NACA66-309 a=0.2
20. NACA65-411 a=0.0
21. NACA65-410 a=0.2