Airfoil Data
HQ2195

The HQ 2.1/9.5 AIRFOIL is a thin 6.7% chord-thickness airfoil with a maximum camber of 3.3% at 35% chord, suited to high-speed UAVs, sailplane tip sections, and propeller blade design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -3.3°.

Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 54 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 HQ2195 typically compare it against profiles of similar thickness: SIKORSKY SC2110 AIRFOIL, NASA/LANGLEY RC-10(B)3 AIRFOIL, GOE 416A AIRFOIL, E224 (10.17%), GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL. The AG16 is another reference profile frequently considered alongside it.