Similarly shaped airfoils to EPPLER 397
New! Bulk download of polars in Excel format: e397.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. RAF 32
3. EPPLER 399
4. GOE 567
5. EPPLER 395
6. GOE 430
7. GOE 497
8. Joukowsky 14.00% thick 5.00% camber
9. NACA63-714 a=0.8
10. MID 403
11. NACA63-713 a=0.8
12. GOE 412
13. Joukowsky 14.00% thick 6.00% camber
14. NACA64-714 a=0.8
15. GOE 414
16. EPPLER 210
17. NACA64-713 a=0.8
18. FX 63-137 13.7% smoothed
19. Joukowsky 15.00% thick 5.00% camber
20. Joukowsky 13.00% thick 5.00% camber
21. NACA63A713