What is the lift coefficient of a flat wing?

The lift coefficient of a flat wing, often referred to as a flat plate, typically ranges from about 0.5 to 1.0, depending on the angle of attack. At low angles, the lift coefficient is lower, but as the angle increases, it can rise significantly until reaching a maximum before stall occurs. The exact value can vary based on the Reynolds number and flow conditions. For practical applications, detailed aerodynamic analysis or experimental data is often used to determine the lift coefficient for specific configurations.