Similarly shaped airfoils to NYU/GRUMMAN K-1
New! Bulk download of polars in Excel format: k1.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
Dynamic plotter New!
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. RAE 5212
3. RAE 6-9CK
4. RAE 2822
5. BOEING J
6. GOE 416A
7. NACA63-312
8. DSMA-523B
9. NACA63-212 a=0.8
10. NACA64(1)-212
11. NACA64-312
12. NACA64-212 a=0.8
13. WHITCOMB INTEGRAL SUPERCRITICAL
14. NACA63-212
15. DSMA-523A
16. HQ 1.0/12
17. HQ 1.5/12
18. NACA64-212
19. NACA63A212
20. NACA63-211 a=0.8
21. NACA63-311