Similarly shaped airfoils to AH 83-150 Q
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. NACA64-715 a=0.2
3. NACA65-715 a=0.0
4. DEFIANT CANARD BL110
5. NACA65-716 a=0.2
6. NACA64-716 a=0.2
7. NACA65-615 a=0.5
8. NACA63-715 a=0.2
9. FX 84-W-150
10. NACA64-715 a=0.0
11. NACA65-615 a=0.2
12. NACA65-714 a=0.2
13. NACA63-716 a=0.2
14. NACA64-615 a=0.5
15. GA 40-615
16. NACA65-716 a=0.0
17. AH 81-K-144/17
18. cristal_cb85_15_7
19. GA 40A615
20. NACA65-616 a=0.5
21. AH 94-156