Similarly shaped airfoils to Ritz 1-30-12
New! Bulk download of polars in Excel format: Ritz%201-30-12.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. NPL 9627
3. MJZ1211
4. NPL 9626
5. NPL 9660
6. NPL 9615
7. ONERA NACA CAMBRE
8. HQ 1.0/12
9. NACA63-212 a=0.0
10. NACA63-212 a=0.2
11. NACA64-212 a=0.0
12. Horten 11.00% thick 1.00% camber
13. NACA64-212 a=0.2
14. NACA63-212
15. NACA63A112
16. NACA63A212
17. NACA64-212
18. NACA23012
19. NACA63-112 a=0.5
20. NACA63-112 a=0.6
21. NACA63-212 a=0.5