Similarly shaped airfoils to Joukowsky 12.00% thick 1.00% camber
New! Bulk download of polars in Excel format: Joukowsky%2012.00%25%20thick%201.00%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 11.00% thick 1.00% camber
3. Joukowsky 13.00% thick 1.00% camber
4. GOE 416A
5. JWL081 11/1.3
6. EPPLER 426
7. EPPLER 428
8. NACA63-212
9. HQ 1.0/12
10. HM50
11. NACA63-211
12. MJZ1211
13. NACA63-212 a=0.8
14. GOE 767
15. Horten 11.00% thick 1.00% camber
16. NACA63-212 a=0.6
17. NACA63-112 a=0.6
18. NACA63-212 a=0.0
19. NACA1412
20. NACA63-112 a=0.8
21. NACA63-212 a=0.5