Airfoil Data
KC135B

The KC-135 BL124.32 AIRFOIL is a thin 7.9% chord-thickness airfoil with a maximum camber of 4.0% 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 -4.0°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 58 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 KC135B typically compare it against profiles of similar thickness: WORTMANN FX 082-512 AIRFOIL, SELIG 3002-099-83, NACA 2.5411, HOBIE, GOE 484 AIRFOIL. The GOE 775 AIRFOIL is another reference profile frequently considered alongside it.