Airfoil Data
LS413MOD

The NASA/LANGLEY LS(1)-0413MOD AIRFOIL is a 8.5% chord-thickness airfoil with a maximum camber of 4.3% at 35% 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 -4.3°.

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.

Designers evaluating the LS413MOD typically compare it against profiles of similar thickness: SD7032-099-88, AS5045 (15%) | Ref: http://www.krnet.org/as504x/ [original link: http://amber.aae.uiuc.edu/~ashok/kr2/airfoils/tests/], EPPLER 335 AIRFOIL, GOE 257 AIRFOIL, AS6095 | Ananda-Selig | AIAA Paper 2018-0310. The S2091-101-83 is another reference profile frequently considered alongside it.