Airfoil Data
LS413
NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL
Wing Geometry Simulator
The NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL is a 8.5% chord-thickness airfoil with a maximum camber of 4.2% at 43% 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 -4.2°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 59 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The slim profile minimises pressure drag at higher speeds but leaves limited spar depth for structural integration.
The LS413 appears in the wing design of at least 3 documented aircraft, including designs from National and PIK-26. Its proven track record across rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the LS413 typically compare it against profiles of similar thickness: N-9, GOE 379 AIRFOIL, A18 (original), GOE 328 AIRFOIL, MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYBRID). The NACA 66(2)-215 is another reference profile frequently considered alongside it.
Aircraft Using the LS413 Airfoil
National Aerospace Laboratories/Taneja Nalla-2 Hansa | National | NASA LS(1)-0415 | NASA LS(1)-0413 |
National Aerospace Laboratories/Taneja Nalla-3 Hansa | National | NASA LS(1)-0415 | NASA LS(1)-0413 |
PIK-26 | PIK-26 | NASA LS(1)-0413 | Constant |
Wing lofting: 2 of these aircraft taper from LS413 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 LS413 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.5%) and max camber (4.2%).