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
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. 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