Similarly shaped airfoils to Joukowsky 13.00% thick 1.00% camber
New! Bulk download of polars in Excel format: Joukowsky%2013.00%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 12.00% thick 1.00% camber
3. Joukowsky 14.00% thick 1.00% camber
4. HQ 1.0/12
5. NACA1412
6. MJZ1211
7. NACA63-213
8. MH 106 13.07%
9. NACA63-212
10. NACA63-213 a=0.8
11. NACA63-213 a=0.6
12. GOE 766
13. NPL 9627
14. NACA63-213 a=0.5
15. NACA64(1)-212 MOD B
16. Ritz 1-30-12
17. NACA63-213 a=0.0
18. NACA63-212 a=0.8
19. NACA63-113 a=0.6
20. NACA63-113 a=0.8
21. NACA63-213 a=0.2