Rosner t=30.0 f=11.0, rN=0.9, te=10.4
New! Bulk download of polars in Excel format: Rosner%20t%3D30.0%20f%3D11.0%2C%20rN%3D0.9%2C%20te%3D10.4.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.
DB Name: Rosner t=30.0 f=11.0, rN=0.9, te=10.4
Family: Rosner
Max thickness: 11.0% at x = 30.06% chord
Max camber: 0.0% at x = 53.98% chord
Available data sources:
XFOIL ncrit=9
XFOIL ncrit=5
XFOIL ncrit=12
JavaFoil+Calcfoil stall+Eppler ext transition
NF ncrit=5
NF ncrit=9
NF ncrit=12
Notes:
https://www.rcgroups.com/forums/showpost.php?p=55219157&postcount=7