Airfoil Data
APEX16_NASA_CR-201062

The APEX 16 is a 8.9% chord-thickness airfoil with a maximum camber of 4.5% at 42% 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 -4.5°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 60 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 APEX16_NASA_CR-201062 typically compare it against profiles of similar thickness: GOE 117 (MVA MK.4) AIRFOIL, GOE 79 (PFALZ 11) AIRFOIL, LOCKHEED L-188 ROOT AIRFOIL, AS6096 | Ananda-Selig | AIAA Paper 2018-0310, NACA 2414. The HAWKER TEMPEST 37.5% SEMISPAN AIRFOIL is another reference profile frequently considered alongside it.