Airfoil Data
C141D
LOCKHEED C-141 BL610.61 AIRFOIL
Wing Geometry Simulator
The LOCKHEED C-141 BL610.61 AIRFOIL is a thin 6.9% chord-thickness airfoil with a maximum camber of 3.4% at 40% chord, suited to high-speed UAVs, sailplane tip sections, and propeller blade design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -3.4°.
Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 55 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 C141D typically compare it against profiles of similar thickness: HQ 3.0/8 AIRFOIL, EPPLER 521 AIRFOIL, GOE 142 (MVA H.19) AIRFOIL, NACA 2410, HQ 2.5/9 AIRFOIL. The FX 84-W-175 is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the C141D frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (6.9%) and max camber (3.4%).
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