Similarly shaped airfoils to KC-135 BL124.32
New! Bulk download of polars in Excel format: kc135b.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. NACA65-213 a=0.2
3. NACA64-213 a=0.0
4. NACA64-213 a=0.2
5. NACA65-113 a=0.5
6. NACA65-113 a=0.2
7. NACA65-113 a=0.6
8. NACA63-213 a=0.0
9. NACA65-113 a=0.0
10. NACA64-214 a=0.0
11. NACA64A113
12. NACA63-213 a=0.2
13. NACA64-113 a=0.5
14. RC-12(N)1
15. NACA65-212 a=0.0
16. NACA64-113 a=0.2
17. NACA64-214 a=0.2
18. NACA65-113 a=0.8
19. NACA63A113
20. NACA65-214 a=0.0
21. HAWKER TEMPEST 61% SEMISPAN