Similarly shaped airfoils to HG 41
New! Bulk download of polars in Excel format: HG%2041.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. HG 40
3. SSV2316 VANS RV-10
4. HG 43
5. GOE 738
6. MH 104 15.28%
7. NACA63-415 a=0.2
8. NACA63-415 a=0.0
9. NACA63-515 a=0.0
10. MID 371AW
11. Horten 14.00% thick 4.00% camber
12. Horten 14.00% thick 3.00% camber
13. NACA64-415 a=0.2
14. DAVIS BASIC B-24 WING
15. NACA63-414 a=0.0
16. NACA63-414 a=0.2
17. NACA64-415 a=0.0
18. NACA64-515 a=0.0
19. Horten 15.00% thick 4.00% camber
20. NACA63-516 a=0.0
21. NACA63-416 a=0.2