Airfoil Data
GOE430

The GOE 430 AIRFOIL is a 10.8% chord-thickness airfoil with a maximum camber of 5.4% at 40% 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 -5.4°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 66 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

The GOE430 appears in the wing design of at least 4 documented aircraft, including designs from Dewoitine and Latecoere. Its proven track record across conventional and rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the GOE430 typically compare it against profiles of similar thickness: GOE 330 (PFALZ 59) AIRFOIL, GOE 190 (MVA MK.18) AIRFOIL, NASA/LANGLEY LS(1)-0417MOD AIRFOIL, FX 61-163 AIRFOIL, FX 60-160 AIRFOIL. The AS6095 | Ananda-Selig | AIAA Paper 2018-0310 is another reference profile frequently considered alongside it.