Airfoil Data
GOE529
GOE 529 AIRFOIL
Wing Geometry Simulator
The GOE 529 AIRFOIL is a 10.5% chord-thickness airfoil with a maximum camber of 5.2% 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 -5.2°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 65 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 10% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The GOE529 appears in the wing design of at least 1 documented aircraft — notably by Klemm. Its proven track record across rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the GOE529 typically compare it against profiles of similar thickness: EPPLER 545 AIRFOIL, AH 80-129, NACA 747A415, NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL, NACA 16-021. The HQ 2.5/9 B AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the GOE529 Airfoil
Klemm L20 | Klemm | Goettingen 527 | Goettingen 529 |
Wing lofting: 1 of these aircraft taper from GOE529 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 GOE529 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.5%) and max camber (5.2%).