Similarly shaped airfoils to Joukowsky 13.00% thick 2.00% camber
New! Bulk download of polars in Excel format: Joukowsky%2013.00%25%20thick%202.00%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 14.00% thick 2.00% camber
3. SB98 VR5 root
4. HN-1069a
5. NACA63-313 a=0.8
6. SB95 11.5/2
7. MID 327 12%
8. NACA63-413
9. HN-980
10. HQ 2.0/12
11. HN-1091a
12. CB2012
13. HN-1091
14. NACA63-312 a=0.8
15. NACA63-313 a=0.6
16. NACA2412
17. HQ 1.5/12
18. NACA63-412
19. GA 30-212
20. HN-1069b
21. GA 35-213