Airfoil Data
DOA5
DORNIER A-5 AIRFOIL
Wing Geometry Simulator
The DORNIER A-5 AIRFOIL is a 9.9% chord-thickness airfoil with a maximum camber of 5.0% at 42% 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 -5.0°.
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 DOA5 appears in the wing design of at least 9 documented aircraft, including designs from Dornier and Fairchild. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the DOA5 typically compare it against profiles of similar thickness: GOE 593 AIRFOIL, MB253515 15.0% smoothed, GEMINI (smoothed), LISSAMAN 7769 AIRFOIL, GOE 746 AIRFOIL. The GOE 436 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the DOA5 Airfoil
Dornier Do 228 | Dornier | Do A-5 | Constant |
Dornier Do 24 ATT | Dornier | Do A-5 | Constant |
Dornier Do 328 | Dornier | Do A-5 | Constant |
Dornier TNT | Dornier | Do A-5 | Constant |
Fairchild Dornier 328 | Fairchild | Do A-5 | Constant |
Fairchild Dornier 328JET | Fairchild | Do A-5 | Constant |
Fairchild Dornier 428JET | Fairchild | Do A-5 | Constant |
Hindustan Aeronautics Ltd 228 | Hindustan | Do A-5 | Constant |
Tupolev Tu-136 | Tupolev | Do A-5 | Constant |
Related Airfoils
Engineers evaluating the DOA5 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (9.9%) and max camber (5.0%).