Similarly shaped airfoils to DP1.87/9.07_DS
New! Bulk download of polars in Excel format: DP1.87_9.07_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. DP2.05/8.65_DS
3. DP1.68/8.37_DS
4. NACA66-309 a=0.5
5. BOEING 707 .99 SPAN
6. NACA66-309 a=0.2
7. NACA66-309 a=0.6
8. GA 40A210
9. GA 37A210
10. NACA65A309
11. BOEING 707 .54 SPAN
12. GA 40-210
13. NACA65-309 a=0.5
14. KC-135 BL351.6
15. NACA65-310 a=0.5
16. DP1.77/8.23_DS
17. NACA66-309 a=0.0
18. NACA65-309 a=0.6
19. DP1.72/8.32_DS
20. NACA65-309 a=0.2
21. DP1.82/8.21_DS