Similarly shaped airfoils to P-51D TIP (BL215)
New! Bulk download of polars in Excel format: p51dtip.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. NACA65-211 a=0.8
3. NACA65-211 a=0.5
4. NACA66A211
5. NACA66-211 a=0.6
6. NACA66-211 a=0.8
7. NACA66-211 a=0.5
8. NACA65A211
9. NACA65-211
10. NACA65-212 a=0.6
11. NACA65-212 a=0.8
12. NACA66-211
13. NACA65-212 a=0.5
14. NACA65(1)-212
15. NACA65-211 a=0.2
16. NACA66-211 a=0.2
17. NACA65-311
18. NACA65-212
19. NACA65(1)-212 a=0.6
20. NACA65-211 a=0.0
21. NACA64A211