Similarly shaped airfoils to DP2.06/8.67_DS
New! Bulk download of polars in Excel format: DP2.06_8.67_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. NACA66-309 a=0.5
3. DP1.87/9.07_DS
4. NACA65-309 a=0.5
5. NACA66-309 a=0.6
6. DP1.82/8.21_DS
7. DP2.00/8.55_DS
8. DP1.77/8.23_DS
9. NACA65-309 a=0.6
10. BOEING 707 .99 SPAN
11. DP1.68/8.37_DS
12. NACA66-309 a=0.2
13. DP1.72/8.16_DS
14. RK40
15. NACA65-309 a=0.2
16. NACA65A309
17. DP1.72/8.32_DS
18. BOEING 707 .54 SPAN
19. DP1.79/8.37_DS
20. KC-135 BL351.6
21. NACA66-409 a=0.0