Similarly shaped airfoils to AH 79-K-132/20
New! Bulk download of polars in Excel format: ah79k132.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. NACA65-514 a=0.5
3. GA 40A414
4. GA 40-414
5. NACA65-513 a=0.5
6. AH 93-K-130/15
7. NACA65-614 a=0.5
8. NACA65-614 a=0.2
9. GA 37A414
10. AH 93-K-131/15
11. NACA65-613 a=0.2
12. GA 40A413
13. NACA65-514 a=0.6
14. AH 63-K-127/24
15. GA 40-413
16. AH 93-K-132/15
17. GA 37A413
18. NACA66-513 a=0.5
19. NACA65-513 a=0.6
20. FX 74-130 WP2 MOD
21. AH 79-K-135/20 B