Similarly shaped airfoils to DP2.05/8.65_DS
New! Bulk download of polars in Excel format: DP2.05_8.65_DS.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. DP2.00/8.55_DS
3. NACA66-309 a=0.5
4. DP1.87/9.07_DS
5. NACA66-309 a=0.6
6. DP1.77/8.23_DS
7. DP1.82/8.21_DS
8. RK40
9. BOEING 707 .99 SPAN
10. NACA65-309 a=0.5
11. DP1.72/8.16_DS
12. NACA65-309 a=0.6
13. DP1.79/8.37_DS
14. NACA66-409 a=0.0
15. DP1.68/8.37_DS
16. DP1.72/8.32_DS
17. NACA66-309 a=0.2
18. NACA65A309
19. NACA67-309 a=0.5
20. FX 69-H-083
21. NACA66-309 a=0.8