Airfoil Data
FX73CL1152
FX 73-CL1-152
Wing Geometry Simulator
The FX 73-CL1-152 is a 13.4% chord-thickness airfoil with a maximum camber of 6.7% at 28% chord, suited to high-lift UAV wings, RC sailplanes, and low-Reynolds-number slow-flyers. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -6.7°.
Thin airfoil theory predicts a stall angle near 11.1° and a peak lift-to-drag ratio around 71 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 13% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The FX73CL1152 appears in the wing design of at least 1 documented aircraft — notably by Glasfaser. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the FX73CL1152 typically compare it against profiles of similar thickness: FX S 02-196 AIRFOIL, GOE 628 AIRFOIL, AH 95-160, FX 76-MP-120, AUGUST 160. The FX 73-K-170/22 is another reference profile frequently considered alongside it.
Aircraft Using the FX73CL1152 Airfoil
Glasfaser Velino | Glasfaser | Wortmann FX 73-CL 1-152 | Constant |
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Engineers evaluating the FX73CL1152 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (13.4%) and max camber (6.7%).
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