DU 86-137/25
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: du861372
Family: Delft
Max thickness: 13.7% at x = 39.72% chord
Max camber: 0.2% at x = 9.71% chord
Available data sources:
JavaFoil+Calcfoil stall+Eppler ext transition
XFOIL ncrit=9
Notes:
Coordinates and information in these papers:
Boermans & Bennis, "DESIGN AND WINDTUNNEL TESTS OF AN AIRFOIL FOR THE HORIZONTAL TAILPLANE OF A STANDARD CLASS SAILPLANE," Technical Soaring, Vol 16 No 2 (1992).
Boermans & Bennis, "Errata for 'DESIGN AND WIND TUNNEL TESTS OF AN AIRFOIL FOR THE HORIZONTAL TAILPLANE OF A STANDARD CLASS GLIDER'," Technical Soaring, Vol 17 No 1 (1993).
Boermans & Bennis, "Addition to 'Design and wind tunnel tests of an airfoil for the horizontal tailplane of a Standard Class glider'," Technical Soaring, Vol 17 No 3 (1993).