Airfoil Data
KC135A

The KC-135 BL52.44 AIRFOIL is a 9.2% chord-thickness airfoil with a maximum camber of 4.6% at 35% 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 -4.6°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 61 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 KC135A typically compare it against profiles of similar thickness: ONERA HOR12 AIRFOIL, GOE 803 (HACKLINGER) AIRFOIL, SOMERS S102 AIRFOIL (BLUNT), GOE 613 AIRFOIL, SOMERS S102 AIRFOIL (SHARP). The FX 84-W-150 is another reference profile frequently considered alongside it.