Similarly shaped airfoils to TH 25816 HALE
New! Bulk download of polars in Excel format: th25816.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. FX 83-W-227
3. FX 69-274
4. NACA67-720 a=0.8
5. NACA67A720
6. NACA67-720 a=0.6
7. NACA67-620 a=0.8
8. TsAGI B 25.0% thick
9. NACA67A620
10. NACA67-720
11. TsAGI B 24.5% thick
12. NACA67-720 a=0.5
13. NACA67-620 a=0.6
14. TsAGI B 24.0% thick
15. FX 77-W-270S
16. TsAGI B 23.5% thick
17. NACA67-620 a=0.5
18. FX 77-W-270
19. NACA66-720 a=0.8
20. NACA66A720
21. TsAGI B 23.0% thick