Similarly shaped airfoils to EPPLER 598
New! Bulk download of polars in Excel format: e598.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. FX 77-W-121
3. FAD21
4. LISSAMAN 7769
5. NACA63-711 a=0.2
6. NACA63-711 a=0.0
7. GOE 323 (HANSA-BRANDENBURG V.1)
8. NACA63-710 a=0.2
9. GOE 318 (HANSA-BRANDENBURG VI.5)
10. NACA63-710 a=0.0
11. NACA64-711 a=0.2
12. S4310
13. NACA64-711 a=0.0
14. GOE 385
15. NACA63-611 a=0.2
16. GOE 286
17. AQUILA 9.3% smoothed
18. NACA64-710 a=0.2
19. NACA63-712 a=0.2
20. NACA64-710 a=0.0
21. GOE 316 (HANSA-BRANDENBURG IV.5)