Airfoil Data
KC135B
KC-135 BL124.32 AIRFOIL
Wing Geometry Simulator
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.
Design wings in your spreadsheet
AeroSheet loads KC135B airfoils directly into Google Sheets. Polars, 3D splines, Fusion 360 export, without leaving your spreadsheet.
Install in Google Sheets coming soonRelated Airfoils
Engineers evaluating the KC135B frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (7.9%) and max camber (4.0%).
Need a custom engineering simulator?
The 3D engine on this page is built by Veenie Aerospace. We build bespoke, browser-native digital twins, aerodynamic simulators, and AI physics tools for UAV startups and defense contractors.