Airfoil Data
LS417
NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL
Wing Geometry Simulator
The NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL is a 10.5% chord-thickness airfoil with a maximum camber of 5.3% at 40% 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 -5.3°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 65 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The LS417 appears in the wing design of at least 2 documented aircraft — notably by Adam. Its proven track record across conventional designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the LS417 typically compare it against profiles of similar thickness: NACA 16-021, NACA 66-021 AIRFOIL, NACA 747A415, NACA 0021, EPPLER 545 AIRFOIL. The EPPLER 331 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the LS417 Airfoil
Adam Aircraft A500 | Adam | NASA LS(1)-0417 | Constant |
Adam Aircraft A700 | Adam | NASA LS(1)-0417 | Constant |
Design wings in your spreadsheet
AeroSheet loads LS417 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 LS417 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.5%) and max camber (5.3%).
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