Similarly shaped airfoils to NACA 1-H-15
New! Bulk download of polars in Excel format: n1h15.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. NACA65-715 a=0.5
3. NACA66-714 a=0.5
4. NACA65-714 a=0.5
5. FX 67-K-150/17
6. NACA66-715 a=0.5
7. NACA65-715 a=0.6
8. NACA65-716 a=0.5
9. FX 78-K-140/20
10. NACA66-714 a=0.6
11. NACA64-715 a=0.5
12. NACA65-714 a=0.6
13. NACA66-713 a=0.5
14. NACA66-715 a=0.6
15. AH 94-145
16. GA 40-615
17. GA 40A615
18. NACA65-716 a=0.6
19. FX 78-K-140 A/20
20. NACA64-714 a=0.5
21. NACA64-716 a=0.5