Similarly shaped airfoils to NACA M8 (NACA-TR-221)
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
Dynamic plotter New!
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. NACA M17 (NACA-TR-221)
3. NACA65-709 a=0.2
4. NACA64-709 a=0.2
5. GOE 314 (HANSA-BRANDENBURG)
6. GOE 316 (HANSA-BRANDENBURG IV.5)
7. NACA63-709 a=0.2
8. NACA M14
9. GOE 308 (MVA H.40)
10. GOE 188
11. GOE 328
12. GOE 257
13. GOE 287
14. NACA65-709 a=0.0
15. GOE 315 (HANSA-BRANDENBURG III.5)
16. GOE 408
17. NACA64-709 a=0.0
18. GOE 318 (HANSA-BRANDENBURG VI.5)
19. GOE 310 (MVA H.42)
20. GOE 277 (DAIMLER VIII)
21. NACA63-709 a=0.0