Similarly shaped airfoils to AH 94-156
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. AH 83-159
3. cristal_cb85_15_7
4. NACA65-616 a=0.5
5. HORSTMANN AND QUAST HQ-300 GD(MOD 2)
6. NACA65-616 a=0.6
7. NACA66-616 a=0.5
8. NACA66-615 a=0.5
9. AH 82-150 F
10. NACA65-617 a=0.5
11. GA 40A416
12. GA 40-416
13. NACA66-616 a=0.6
14. FX 78-K-150/20
15. GA 37A416
16. MRC-20
17. NACA66-615 a=0.6
18. NACA65-617 a=0.6
19. GA 40A616
20. NACA65-716 a=0.2
21. GA 40-616