Airfoil Data
AS6099
AS6099 | Ananda-Selig | AIAA Paper 2018-0310
Wing Geometry Simulator
The AS6099 | Ananda-Selig | AIAA Paper 2018-0310 is a 10.2% chord-thickness airfoil with a maximum camber of 5.1% at 36% 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 -5.1°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 64 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 10% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the AS6099 typically compare it against profiles of similar thickness: EPPLER 556 AIRFOIL, EPPLER 715 AIRFOIL, AH 93-K-131/15, AH 80-136, FX 60-157 AIRFOIL. The SD7090 (10%) is another reference profile frequently considered alongside it.
Design wings in your spreadsheet
AeroSheet loads AS6099 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 AS6099 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.2%) and max camber (5.1%).
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.