Airfoil Data
NLR7301

The NLR-7301 AIRFOIL is a 8.8% chord-thickness airfoil with a maximum camber of 4.4% 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 -4.4°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 60 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 NLR7301 typically compare it against profiles of similar thickness: E209 (13.72%), EPPLER 332 AIRFOIL, GOE 325 (PFALZ 54) AIRFOIL, GOE 326 (PFALZ 55) AIRFOIL, GOE 286 AIRFOIL. The MH 83 13.29% is another reference profile frequently considered alongside it.