Similarly shaped airfoils to AH 63-K-127/24
New! Bulk download of polars in Excel format: ah63k127.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 74-130 WP2
3. NACA65-613 a=0.6
4. NACA65-613 a=0.5
5. AH 80-129
6. NACA65-713
7. NACA65-513 a=0.6
8. FX 84-W-127
9. NACA65-613 a=0.8
10. AH 79-K-132/20
11. NACA65-513 a=0.5
12. GA 40-413
13. GA 40A413
14. NACA64-613 a=0.6
15. NACA65-612 a=0.6
16. NACA65-512 a=0.6
17. NACA65-612 a=0.5
18. NACA64-613 a=0.5
19. NACA64A613
20. AH 88-K-130/20
21. NACA65-712