Airfoil Data
TH25816
TH 25816 HALE AIRFOIL
Wing Geometry Simulator
The TH 25816 HALE AIRFOIL is a thick 16.8% chord-thickness airfoil with a maximum camber of 8.4% at 48% 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 -8.4°.
Thin airfoil theory predicts a stall angle near 9.9° and a peak lift-to-drag ratio around 75 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 17% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The TH25816 appears in the wing design of at least 1 documented aircraft — notably by Aurora. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the TH25816 typically compare it against profiles of similar thickness: FX74_CL5_140, WORTMANN FX 72-MS-150B AIRFOIL, FX 69-274, GOE 390 AIRFOIL, GOE 241 (MVA PR.1) AIRFOIL. The GOE 525 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the TH25816 Airfoil
Aurora Flight Sciences Theseus | Aurora | Drela TH-25/TH-26B | Drela TH-28A |
Wing lofting: 1 of these aircraft taper from TH25816 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 TH25816 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (16.8%) and max camber (8.4%).