Airfoil Data
DAVIS_CORRECTED
DAVIS BASIC B-24 WING AIRFOIL
Wing Geometry Simulator
The DAVIS BASIC B-24 WING AIRFOIL is a 10.4% 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.
Designers evaluating the DAVIS_CORRECTED typically compare it against profiles of similar thickness: I.S.A. 960, AH 88-K-130/20, NASA NLF(1)-0416, 74-130 WP2, GOE 500 AIRFOIL. The GOE 797 AIRFOIL is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the DAVIS_CORRECTED frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.4%) and max camber (5.2%).
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