Similarly shaped airfoils to HL80-133
New! Bulk download of polars in Excel format: HL80-133.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. NACA63-614 a=0.0
3. NACA64-614 a=0.0
4. NACA63-514 a=0.2
5. NACA64-514 a=0.2
6. BOEING 106
7. MS3-14Retro
8. GA 30-413.5
9. NACA63-614 a=0.2
10. NACA64-614 a=0.2
11. GA 30-413
12. GA 35A414
13. EPPLER 329
14. S4233-136-84
15. S2027
16. MS3-13Retro
17. GA 30A413
18. NACA63-513 a=0.2
19. NACA64-513 a=0.2
20. NACA65-514 a=0.2
21. NACA63-613 a=0.0