Airfoil Data
DAI1335
DAI 1335
Wing Geometry Simulator
The DAI 1335 is a 12.9% chord-thickness airfoil with a maximum camber of 6.5% at 38% 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 -6.5°.
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 DAI1335 appears in the wing design of at least 2 documented aircraft, including designs from McIntyre and MIT. Its proven track record across rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the DAI1335 typically compare it against profiles of similar thickness: EPPLER 561 AIRFOIL, GOE 797 AIRFOIL, FX 73-K-170/22, USA 98 AIRFOIL, GOE 683 AIRFOIL. The GOE 567 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the DAI1335 Airfoil
McIntyre Airglow | McIntyre | Drela DAI 1335 | Constant |
MIT Light Eagle | MIT | Drela DAI 1335 | Drela DAI 1336/1238 |
Wing lofting: 1 of these aircraft taper from DAI1335 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 DAI1335 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (12.9%) and max camber (6.5%).