Similarly shaped airfoils to NACA M8 (NACA-TR-221)


New! Bulk download of polars in Excel format: NACA%20M8%20%28NACA-TR-221%29.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
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.

1. GOE 309 (MVA H.41)
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