Similarly shaped airfoils to MID 107
New! Bulk download of polars in Excel format: MID%20107.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. AH 79-100 A
3. FX 60-100
4. FX 60-100 (126)
5. EM J18 3510 26 51
6. OAF095
7. Joukowsky 9.00% thick 4.00% camber
8. Joukowsky 11.00% thick 4.00% camber
9. FX 60-100 10.0% smoothed
10. GOE 602 MOD.
11. OAF102
12. SD7043 (9.1%)
13. NACA63-610 a=0.8
14. MH 116 9.84%
15. NACA63-710
16. NACA63-609 a=0.8
17. FX 63-100
18. RAF 32 MOD
19. NACA63-709
20. MH 38 9.68%
21. GOE 115 (MVA MK.2)