Airfoil Data
FX62K153

The FX 62-K-153/20 AIRFOIL is a 11.5% chord-thickness airfoil with a maximum camber of 5.7% at 43% 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 -5.7°.

Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 68 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

The FX62K153 appears in the wing design of at least 5 documented aircraft, including designs from Akaflieg and Ilmailukerho. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the FX62K153 typically compare it against profiles of similar thickness: AH 94-156, MUE 139, EPPLER 793 AIRFOIL, UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL, EPPLER 551 AIRFOIL. The LA2573A is another reference profile frequently considered alongside it.