Similarly shaped airfoils to LISSAMAN 7769
New! Bulk download of polars in Excel format: l7769.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (4) | 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 598
3. GOE 318 (HANSA-BRANDENBURG VI.5)
4. GOE 746
5. FAD21
6. FX 77-W-121
7. NACA45010
8. NACA45009
9. NACA45010.5
10. NACA63-610 a=0.2
11. NACA63-710 a=0.0
12. GOE 316 (HANSA-BRANDENBURG IV.5)
13. NACA63-610 a=0.0
14. NACA63-711 a=0.0
15. Horten 10.00% thick 5.00% camber
16. NACA63-611 a=0.2
17. AQUILA 9.3% smoothed
18. GOE 286
19. NACA45110
20. Horten 9.00% thick 5.00% camber
21. NACA64-610 a=0.2