Similarly shaped airfoils to Joukowsky 11.00% thick 4.00% camber
New! Bulk download of polars in Excel format: Joukowsky%2011.00%25%20thick%204.00%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 12.00% thick 4.00% camber
3. EM J18 3510 26 51
4. AH 79-100 A
5. MID 107
6. MS535-3V
7. FX 60-100
8. FX 60-100 (126)
9. RAF 32 MOD
10. FX 83-W-108
11. OAF102
12. MH 116 9.84%
13. EPPLER 393
14. NACA63-611 a=0.8
15. FX 60-100 10.0% smoothed
16. GOE 602 MOD.
17. MH 38 9.68%
18. GOE 546
19. GOE 723
20. NACA63-711
21. FX 60-126/1