Similarly shaped airfoils to Joukowsky 14.00% thick 1.00% camber
New! Bulk download of polars in Excel format: Joukowsky%2014.00%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 15.00% thick 1.00% camber
3. OAF128
4. NACA63-214
5. NACA63-214 a=0.8
6. NACA63-213
7. NACA63-214 a=0.6
8. Joukowsky 12.00% thick 1.00% camber
9. NACA63-214 a=0.5
10. Joukowsky 16.00% thick 1.00% camber
11. NACA63-213 a=0.8
12. NACA63-214 a=0.2
13. NACA63-214 a=0.0
14. NACA63-114 a=0.6
15. NACA63-114 a=0.8
16. S8038 (13%)
17. Joukowsky 14.00% thick 0.00% camber
18. Joukowsky 14.00% thick 2.00% camber
19. MH 106 13.07%
20. NACA63-114 a=0.5
21. NACA63-213 a=0.6