Similarly shaped airfoils to HM391-1
New! Bulk download of polars in Excel format: HM391-1.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. NACA23010.5
3. JWL081 11/1.3
4. Horten 11.00% thick 2.00% camber
5. Horten 11.00% thick 1.00% camber
6. NACA23110.5
7. GOE 766
8. NACA23010
9. JWL067 11.5/1.7
10. NACA24010.5
11. BOEING-VERTOL V23010-1.58
12. NACA23110
13. LOCKHEED-GEORGIA SUPERCRITICAL
14. NACA22010.5
15. Horten 10.00% thick 2.00% camber
16. Horten 10.00% thick 1.00% camber
17. AMES A-01
18. MH 108 11.98%
19. NACA32010.5
20. REPUBLIC S-3
21. NACA22110.5