Similarly shaped airfoils to SM085013
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. NACA64A209
3. NACA65-209
4. NACA64-209
5. NACA64-209 a=0.8
6. NACA65-209 a=0.8
7. MH 34
8. HQ 1.0/9
9. NACA63-209
10. NACA64-209 a=0.6
11. NACA65-209 a=0.6
12. NACA63-209 a=0.8
13. DU 86-084/18
14. NACA64-209 a=0.5
15. NACA65-209 a=0.5
16. NACA65A209
17. PROPFAN CRUISE MISSILE WING
18. NACA63-209 a=0.6
19. NACA65-209 a=0.2
20. MH 23 8%
21. NACA64-209 a=0.2