Airfoil Data
DAE11
DAE-11 AIRFOIL
Wing Geometry Simulator
The DAE-11 AIRFOIL is a 12.9% chord-thickness airfoil with a maximum camber of 6.4% at 39% chord, suited to high-lift UAV wings, RC sailplanes, and low-Reynolds-number slow-flyers. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -6.4°.
Thin airfoil theory predicts a stall angle near 11.3° and a peak lift-to-drag ratio around 70 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 13% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The DAE11 appears in the wing design of at least 12 documented aircraft, including designs from Nihon and Raven. 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 DAE11 typically compare it against profiles of similar thickness: EPPLER 1210 AIRFOIL, WORTMANN FX 66-17A-175 AIRFOIL, EPPLER 656 AIRFOIL, FX 66-17AII-182 AIRFOIL, FX 66-182 AIRFOIL. The DAE-51 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the DAE11 Airfoil
Nihon University Mowe IX | Nihon | Drela DAE 11 | Constant |
Nihon University Mowe VII | Nihon | Drela DAE 11 | Constant |
Nihon University Mowe VIII | Nihon | Drela DAE 11 | Constant |
Nihon University Mowe X | Nihon | Drela DAE 11 | Drela DAE 21 |
Nihon University Mowe XV | Nihon | Drela DAE 11 | Drela DAE 41 |
Nihon University Sakuzo 1 | Nihon | Drela DAE 11 | Constant |
Nihon University Sakuzo 2 | Nihon | Drela DAE 11 | Constant |
Nihon University Sakuzo 3 | Nihon | Drela DAE 11 | Constant |
Nihon University Sakuzo 4 | Nihon | Drela DAE 11 | Drela DAE 31 |
Raven HPA | Raven | Drela DAE 11/DAE 21 | Drela DAE 31/DAE 41 |
Team Aeroscepsy Sinbad | Team | Drela DAE 11/ DAE 21 | Drela DAE 31 |
University of British Columbia Thunderbird | University | Drela DAE-11 | Constant |
Wing lofting: 5 of these aircraft taper from DAE11 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 DAE11 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (12.9%) and max camber (6.4%).