Airfoil Data
PRANDTL-D-CENTERLINE
Prandtl-D Centerline NASA TP-2016-219072
Wing Geometry Simulator
The Prandtl-D Centerline NASA TP-2016-219072 is a 10.0% chord-thickness airfoil with a maximum camber of 5.0% at 37% chord, suited to general-aviation and UAV wing design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -5.0°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 63 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The slim profile minimises pressure drag at higher speeds but leaves limited spar depth for structural integration.
Designers evaluating the PRANDTL-D-CENTERLINE typically compare it against profiles of similar thickness: WB-135/35 13.5% smoothed, S4233-136-84, AH 79-K-143/18, EPPLER 334 AIRFOIL, WORTMANN FX 79-K-144/17 AIRFOIL. The FX 71-L-150/30 AIRFOIL is another reference profile frequently considered alongside it.
Design wings in your spreadsheet
AeroSheet loads PRANDTL-D-CENTERLINE airfoils directly into Google Sheets. Polars, 3D splines, Fusion 360 export, without leaving your spreadsheet.
Related Airfoils
Engineers evaluating the PRANDTL-D-CENTERLINE frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.0%) and max camber (5.0%).
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