Similarly shaped airfoils to Joukowsky 9.00% thick 5.00% camber


New! Bulk download of polars in Excel format: Joukowsky%209.00%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
Dynamic plotter New!
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.

1. Joukowsky 10.00% thick 5.00% camber
2. GOE 195
3. GOE 496
4. NACA5509
5. NACA63-709 a=0.8
6. FX 63-100
7. HL73-650
8. NACA64-709 a=0.8
9. EPPLER 385
10. NACA63-709 a=0.6
11. MID 104
12. GOE 495
13. MID 106
14. NACA63A709
15. Joukowsky 11.00% thick 5.00% camber
16. NACA64-709 a=0.6
17. NACA63-710 a=0.8
18. GOE 456
19. GOE 358
20. GOE 458
21. MID 117