Similarly shaped airfoils to AH 93-W-174
New! Bulk download of polars in Excel format: ah93w174.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 66-17AII-182
3. NACA63-617 a=0.5
4. FX 66-S-171
5. NACA63-617 a=0.6
6. FX 66-17AII-182
7. GA 35-417
8. NACA63-618 a=0.5
9. NACA63-618 a=0.6
10. GOE 290 (MVA 290)
11. SB99A22CO
12. GA 35-418
13. NACA64-617 a=0.5
14. NACA64-617 a=0.6
15. NACA63-717
16. GA 37-417
17. NACA63-617 a=0.8
18. NACA64-618 a=0.5
19. GA 35-617
20. NACA63(3)-618
21. NACA63-718