SSV2316 VANS RV-10
New! Bulk download of polars in Excel format: SSV2316.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (2) | 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.
DB Name: SSV2316
Family: Uncategorized
Max thickness: 15.9% at x = 30.00% chord
Max camber: 2.6% at x = 28.18% chord
Available data sources:
JavaFoil+Calcfoil stall+Eppler ext transition
XFOIL ncrit=9
Notes:
Coordinates from a post by David Carr on VansAirForce Forums, rotated by BigFoil to place the trailing edge at y=0 https://vansairforce.net/community/showpost.php?p=428265&postcount=12
http://oscar.dcarr.org/tmp/10wing.txt