Similarly shaped airfoils to Joukowsky 9.00% thick 5.00% camber
New! Bulk download of polars in Excel format: Joukowsky%209.00%25%20thick%205.00%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. GOE 195
3. GOE 496
4. NACA5509
5. NACA63-709 a=0.8
6. FX 63-100
7. HL73-650
8. NACA64-709 a=0.8
9. EPPLER 385
10. NACA63-709 a=0.6
11. MID 104
12. GOE 495
13. MID 106
14. NACA63A709
15. Joukowsky 11.00% thick 5.00% camber
16. NACA64-709 a=0.6
17. NACA63-710 a=0.8
18. GOE 456
19. GOE 358
20. GOE 458
21. MID 117