Airfoil Data
BOE103
BOEING 103 AIRFOIL
Wing Geometry Simulator
The BOEING 103 AIRFOIL is a 9.8% chord-thickness airfoil with a maximum camber of 4.9% at 30% 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 -4.9°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 63 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 BOE103 appears in the wing design of at least 6 documented aircraft — notably by Boeing. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the BOE103 typically compare it against profiles of similar thickness: MRC12, GOE 738 AIRFOIL, S8036 (16%), MH 78 14.47%, AH 88-K-136/16. The HT34 is another reference profile frequently considered alongside it.
Aircraft Using the BOE103 Airfoil
Boeing 204 | Boeing | Boeing 103 | Constant |
Boeing 40A | Boeing | Boeing 103 | Constant |
Boeing 40B | Boeing | Boeing 103 | Constant |
Boeing 40C | Boeing | Boeing 103 | Constant |
Boeing 69 F2B-1 | Boeing | Boeing 103A (upper) | Boeing 103 (lower) |
Boeing Canada A-213 Totem | Boeing | Boeing 103 | Constant |
Wing lofting: 1 of these aircraft taper from BOE103 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 BOE103 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (9.8%) and max camber (4.9%).