Similarly shaped airfoils to cristal_cb85_15_7
New! Bulk download of polars in Excel format: cristal_cb85_15_7.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. GA 40A416
3. AH 83-159
4. AH 94-156
5. AH 82-150 A
6. NACA65-516 a=0.5
7. GA 37A416
8. NACA65-516 a=0.6
9. GA 40-415
10. GA 40A415
11. GA 37-416
12. GA 35A416
13. AH 93-156
14. NACA65-616 a=0.5
15. GA 37A415
16. NACA65-515 a=0.5
17. HORSTMANN AND QUAST HQ-300 GD(MOD 2)
18. NACA65-616 a=0.2
19. NACA65-515 a=0.6
20. GA 35A415
21. GA 40-417