Airfoil Data
DAE41
DAE 41
Wing Geometry Simulator
The DAE 41 is a 8.8% chord-thickness airfoil with a maximum camber of 4.4% 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 -4.4°.
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.
The DAE41 appears in the wing design of at least 2 documented aircraft, including designs from Nihon and Raven. Its proven track record across rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the DAE41 typically compare it against profiles of similar thickness: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL, AH-7-47-6 AIRFOIL, GOE 195 AIRFOIL, MH 116 9.84%, EPPLER 417 AIRFOIL. The DAE-51 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the DAE41 Airfoil
Nihon University Mowe XV | Nihon | Drela DAE 11 | Drela DAE 41 |
Raven HPA | Raven | Drela DAE 11/DAE 21 | Drela DAE 31/DAE 41 |
Wing lofting: 2 of these aircraft taper from DAE41 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 DAE41 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.8%) and max camber (4.4%).