Airfoil Data
FX73CL2152

The FX 73-CL2-152 is a 13.6% chord-thickness airfoil with a maximum camber of 6.8% at 31% 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 -6.8°.

Thin airfoil theory predicts a stall angle near 11.0° 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 14% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the FX73CL2152 typically compare it against profiles of similar thickness: GOE 288 AIRFOIL, GOE 234 (MVA CA5) AIRFOIL, SP4621HP, AH 93-W-215, FX 66-S-196 V1 AIRFOIL. The FX 73-CL1-152 is another reference profile frequently considered alongside it.