Similarly shaped airfoils to AQUILA 9.3% smoothed


New! Bulk download of polars in Excel format: aquilasm.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
Dynamic plotter New!
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.
1. GOE 286
2. GOE 316 (HANSA-BRANDENBURG IV.5)
3. GOE 596
4. GOE 385
5. NACA63-710 a=0.0
6. NACA63-709 a=0.0
7. GOE 257
8. GOE 318 (HANSA-BRANDENBURG VI.5)
9. NACA63-710 a=0.2
10. NACA64-710 a=0.0
11. NACA64-709 a=0.0
12. FAD21
13. NACA64-710 a=0.2
14. GOE 490
15. NACA63-709 a=0.2
16. NACA63-609 a=0.2
17. NACA64-709 a=0.2
18. NACA63-610 a=0.2
19. GOE 167 (V.KARMAN PROP.2)
20. NACA64-609 a=0.2
21. GOE 188