Similarly shaped airfoils to NACA63-716
New! Bulk download of polars in Excel format: NACA63-716.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. NACA63-616 a=0.8
3. NACA64-616 a=0.8
4. NACA63-717
5. NACA63-715
6. NACA63-516 a=0.8
7. FX 60-160
8. NACA63(2)-615
9. NACA64-715
10. NACA64-717
11. NACA63-616
12. NACA63-617 a=0.8
13. EM J18 3015 DrW r0,8
14. NACA63-615 a=0.8
15. HQ 3.0/15
16. EM J18 1 3015
17. NN7 MK20
18. NACA64-516 a=0.8
19. NACA64-617 a=0.8
20. GOE 493
21. NACA64-616