NLF-1015
New! Bulk download of polars in Excel format: nlf1015.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.
DB Name: nlf1015
Family: NASA
Max thickness: 15.0% at x = 41.73% chord
Max camber: 4.6% at x = 58.01% chord
Available data sources:
JavaFoil+Calcfoil stall+Eppler ext transition
XFOIL ncrit=9
CFD (Gotten et. al.)
Wind tunnel (Evangelista & Vemuru)
Notes:
Coordinates from UIUC Airfoil Coordinates Database https://m-selig.ae.illinois.edu/ads/coord_database.html
CFD Data from Gotten. et. al., "A Highly Automated Method for Simulating Airfoil Characteristics at low Reynolds Number using a RANS-transition Approach," Deutscher Luft- und Raumfahrtkongress 2019, https://www.dglr.de/publikationen/2020/490026.pdf
Wind tunnel data from Evangelista, R., and Vemuru, C., "Evaluation of an analysis method for low-speed airfoils by comparison with wind tunnel results," 27th Aerospace Sciences Meeting, AIAA, Reston, 1989.