Similarly shaped airfoils to NACA63-709 a=0.8
New! Bulk download of polars in Excel format: NACA63-709%20a%3D0.8.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. NACA63A709
3. NACA64A709
4. NACA65-709 a=0.8
5. NACA5509
6. NACA63-710 a=0.8
7. NACA64-710 a=0.8
8. NACA65A709
9. NACA63-709 a=0.6
10. NACA64-709 a=0.6
11. FX 63-100
12. S4062-095-87
13. NACA65-710 a=0.8
14. NACA63-609 a=0.8
15. NACA63A710
16. NACA64-609 a=0.8
17. NACA65-709 a=0.6
18. NACA64A710
19. Joukowsky 9.00% thick 5.00% camber
20. GOE 117 (MVA MK.4)
21. NACA63-609 a=0.6