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 |
Related 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%).