Similarly shaped airfoils to Joukowsky 10.00% thick 5.00% camber
New! Bulk download of polars in Excel format: Joukowsky%2010.00%25%20thick%205.00%25%20camber.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. Joukowsky 9.00% thick 5.00% camber
3. Joukowsky 11.00% thick 5.00% camber
4. FX 63-100
5. NACA5509
6. NACA5510
7. EPPLER 216
8. FX 63-110
9. NACA63-710 a=0.8
10. NACA63-709 a=0.8
11. GOE 358
12. S4062-095-87
13. GOE 195
14. NACA64-710 a=0.8
15. NACA64-709 a=0.8
16. NACA63-710 a=0.6
17. NACA63-709 a=0.6
18. S4320
19. Joukowsky 12.00% thick 5.00% camber
20. GOE 392
21. NACA63A709