Airfoil Data
RAF6PROP_SM
RAF 6 AIRFOIL, 12%, LE rad. 0.012, TE rad. 0.0092, NACA TR259 smoothed
Wing Geometry Simulator
The RAF 6 AIRFOIL, 12%, LE rad. 0.012, TE rad. 0.0092, NACA TR259 smoothed is a 12.0% chord-thickness airfoil with a maximum camber of 6.0% 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 -6.0°.
Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 69 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 12% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the RAF6PROP_SM typically compare it against profiles of similar thickness: Bambino 6, GOE 703 AIRFOIL, NACA 0024, DAE-31 AIRFOIL, EPPLER 1214 AIRFOIL. The RONCZ R1145MS MAIN ELEMENT is another reference profile frequently considered alongside it.
Design wings in your spreadsheet
AeroSheet loads RAF6PROP_SM 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 RAF6PROP_SM frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (12.0%) and max camber (6.0%).
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.