Similarly shaped airfoils to AH 94-156
New! Bulk download of polars in Excel format: ah94156.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. DU 99-146
4. cristal_cb85_15_7
5. NACA65-616 a=0.5
6. HORSTMANN AND QUAST HQ-300 GD(MOD 2)
7. NACA65-616 a=0.6
8. NACA66-616 a=0.5
9. NACA66-615 a=0.5
10. AH 82-150 F
11. NACA65-617 a=0.5
12. GA 40A416
13. GA 40-416
14. NACA66-616 a=0.6
15. FX 78-K-150/20
16. GA 37A416
17. MRC-20
18. NACA66-615 a=0.6
19. NACA65-617 a=0.6
20. GA 40A616
21. NACA65-716 a=0.2