Similarly shaped airfoils to Joukowsky 15.00% thick 1.00% camber
New! Bulk download of polars in Excel format: Joukowsky%2015.00%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 16.00% thick 1.00% camber
3. NACA63-215
4. Joukowsky 13.00% thick 1.00% camber
5. Joukowsky 17.00% thick 1.00% camber
6. NACA63-215 a=0.8
7. NACA63-214
8. Joukowsky 15.00% thick 2.00% camber
9. Joukowsky 15.00% thick 0.00% camber
10. NACA63-215 MOD B
11. NACA63-215 a=0.6
12. NACA63-215 a=0.5
13. NACA63-214 a=0.8
14. NACA63-215 a=0.2
15. NACA63-115 a=0.6
16. NACA63-215 a=0.0
17. MID 455
18. NACA63-115 a=0.8
19. NACA63-214 a=0.6
20. NACA63-115 a=0.5
21. NACA63-214 a=0.5