Similarly shaped airfoils to FX 84-W-150
New! Bulk download of polars in Excel format: fx84w150.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. GA 37A615
3. FX 84-W-140
4. GA 37-616
5. GA 37-615
6. NACA64-615 a=0.6
7. NACA65-615 a=0.6
8. GA 40-615
9. GA 40A615
10. NACA65-615 a=0.5
11. NACA64-615 a=0.5
12. NACA64-616 a=0.6
13. AH 81-K-144/17
14. GA 35-616
15. GA 35-615
16. NACA63-615 a=0.6
17. GA 30-615
18. GA 30U-615
19. GA 35A616
20. NACA64-616 a=0.5
21. NACA63-615 a=0.5