Similarly shaped airfoils to AH 93-156
New! Bulk download of polars in Excel format: ah93156.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
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2. AH 83-159
3. NACA65-616 a=0.5
4. NACA66-616 a=0.5
5. DU 99-146
6. cristal_cb85_15_7
7. NACA65-617 a=0.5
8. HORSTMANN AND QUAST HQ-300 GD(MOD 2)
9. NACA66-615 a=0.5
10. NACA65-616 a=0.6
11. NACA66-616 a=0.6
12. NACA65-716 a=0.2
13. GA 40A416
14. NACA66-716 a=0.2
15. NACA65-617 a=0.6
16. GA 37A416
17. GA 40-416
18. NACA65-716 a=0.0
19. AH 82-150 F
20. NACA65-616 a=0.2
21. NACA66-716 a=0.0