Similarly shaped airfoils to MH 18B
New! Bulk download of polars in Excel format: MH%2018B.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
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. NACA65-312 a=0.0
3. NACA64-312 a=0.2
4. NACA64-312 a=0.0
5. NACA65-311 a=0.0
6. NACA65-311 a=0.2
7. Europa Dykins 12%
8. GA 40A212
9. GA 40-212
10. NACA65-312 a=0.5
11. NACA65-412 a=0.0
12. TsAGI B 11.0% thick
13. GA 37A212
14. TsAGI B 11.5% thick
15. NACA65-212 a=0.5
16. NACA63-312 a=0.2
17. RC-12(N)1
18. NACA65(1)-212 a=0.6
19. NACA63-312 a=0.0
20. NACA64-412 a=0.0
21. NACA66-311 a=0.0