Similarly shaped airfoils to NACA63A213
New! Bulk download of polars in Excel format: NACA63A213.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. NACA65-213 a=0.8
3. NACA64-213 a=0.8
4. NACA65-213 a=0.6
5. NACA64-213 a=0.6
6. NACA65-213
7. NACA64-213
8. NACA65-213 a=0.5
9. NACA64-213 a=0.5
10. NACA63-213 a=0.8
11. NACA64-214 a=0.8
12. S8038 (13%)
13. NACA65A213
14. NACA63-213 a=0.6
15. NACA64-313
16. NACA64-214 a=0.6
17. NACA63-213
18. NACA65-313
19. NACA63A214
20. NACA63A212
21. NACA64A214