Airfoil Data
FX67K150
FX 67-K-150/17 AIRFOIL
Wing Geometry Simulator
The FX 67-K-150/17 AIRFOIL is a 12.3% chord-thickness airfoil with a maximum camber of 6.2% at 43% 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 -6.2°.
Thin airfoil theory predicts a stall angle near 11.5° and a peak lift-to-drag ratio around 69 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 12% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The FX67K150 appears in the wing design of at least 39 documented aircraft, including designs from Glasflugel and Schempp-Hirth. Its proven track record across conventional and rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the FX67K150 typically compare it against profiles of similar thickness: NACA M24 AIRFOIL, EPPLER 1230 AIRFOIL, NACA M26 AIRFOIL, FX 66-S-171 AIRFOIL, EPPLER 435 AIRFOIL. The GOE 6K AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the FX67K150 Airfoil
Wing lofting: 27 of these aircraft taper from FX67K150 at the root to a different tip section. Use the Tapered filter to isolate them, then click any tip airfoil link to compare geometries.
Related Airfoils
Engineers evaluating the FX67K150 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (12.3%) and max camber (6.2%).