Similarly shaped airfoils to Pegase coap
New! Bulk download of polars in Excel format: Pegase%20coap.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. EPPLER 1230
3. NACA63-717 a=0.0
4. NACA63-618 a=0.2
5. NACA63-617 a=0.2
6. NACA64-718 a=0.0
7. NACA63-718 a=0.2
8. NACA64-717 a=0.0
9. NACA64-718 a=0.2
10. NACA64-618 a=0.2
11. NACA64-617 a=0.2
12. NACA63-717 a=0.2
13. NACA64-717 a=0.2
14. GOE 290 (MVA 290)
15. GA 35-418
16. GA 30-417
17. GA 35A417
18. GA 37-418
19. NACA63-617 a=0.0
20. GA 35-417
21. NACA63-618 a=0.0