Airfoil Data
LS417MOD
NASA/LANGLEY LS(1)-0417MOD AIRFOIL
Wing Geometry Simulator
The NASA/LANGLEY LS(1)-0417MOD AIRFOIL is a 10.7% chord-thickness airfoil with a maximum camber of 5.4% at 27% 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 -5.4°.
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 LS417MOD appears in the wing design of at least 5 documented aircraft, including designs from Aero Kuhlmann and Nanchang. Its proven track record across conventional and rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the LS417MOD typically compare it against profiles of similar thickness: FX 61-163 AIRFOIL, FX 60-160 AIRFOIL, GOE 330 (PFALZ 59) AIRFOIL, GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL, GOE 633 AIRFOIL. The EPPLER 417 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the LS417MOD Airfoil
Aero Kuhlmann Scub | Aero Kuhlmann | NASA LS(1)-0417MOD | Constant |
Nanchang N-5A | Nanchang | NASA LS(1)-0417MOD | Constant |
Pilatus PC-12 | Pilatus | NASA LS(1)-0417MOD | NASA LS(1)-0313 |
AASI Jetcruzer | AASI | NASA LS(1)-0417MOD | NACA 23012 |
QAC Q200 | QAC | NASA LS(1)-0417MOD | Eppler 1212 |
Wing lofting: 3 of these aircraft taper from LS417MOD at the root to a different tip section. Use the Tapered filter to isolate them, then click any tip airfoil link to compare geometries.
Related Airfoils
Engineers evaluating the LS417MOD frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.7%) and max camber (5.4%).