Similarly shaped airfoils to HQ 3.5/18
New! Bulk download of polars in Excel format: hq3518.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. EPPLER 1200
3. NACA63(3)-618
4. NACA63-618 a=0.8
5. EPPLER 655
6. NACA63-718
7. NACA63-619 a=0.8
8. FX S 02-196
9. NACA63A618
10. NACA63-719
11. EPPLER 1098
12. NACA64-618 a=0.8
13. NACA64-718
14. SB99A22CO
15. NACA64-619 a=0.8
16. NACA64-719
17. Dees Okay230
18. MH 126
19. NACA64-719 a=0.8
20. NACA63-719 a=0.8
21. FX 66-17AII-182