Similarly shaped airfoils to Joukowsky 17.00% thick 4.00% camber
New! Bulk download of polars in Excel format: Joukowsky%2017.00%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 18.00% thick 4.00% camber
3. NM Retro 16
4. MS535-1
5. Joukowsky 17.00% thick 3.00% camber
6. GOE 413
7. Joukowsky 15.00% thick 4.00% camber
8. Joukowsky 19.00% thick 4.00% camber
9. Joukowsky 17.00% thick 5.00% camber
10. FX 66-S-171
11. Joukowsky 16.00% thick 3.00% camber
12. NACA63-617 a=0.8
13. NACA63-616 a=0.8
14. EPPLER 1212
15. Joukowsky 18.00% thick 3.00% camber
16. Joukowsky 18.00% thick 5.00% camber
17. EPPLER 1211
18. EPPLER 559
19. NACA63-717
20. EPPLER 557
21. NACA63-716