What is the angle of attack at which an airplane wing stalls will?

The angle of attack at which an airplane wing stalls is a critical aerodynamic parameter. It's generally between 15 and 20 degrees for typical airfoil designs, but this can vary depending on the specific wing shape.

At this critical angle of attack (https://www.wikiwhat.page/kavramlar/Critical%20Angle%20of%20Attack), the airflow over the upper surface of the wing becomes separated. This flow separation (https://www.wikiwhat.page/kavramlar/Flow%20Separation) drastically reduces lift and increases drag, leading to a stall.

Several factors can influence the stall angle of attack (https://www.wikiwhat.page/kavramlar/Angle%20of%20Attack). These include:

• Airfoil design: Different airfoils stall at different angles.
• Wing shape: Planform, aspect ratio, and twist can all affect stall characteristics.
• Reynolds number: This dimensionless number represents the ratio of inertial forces to viscous forces and influences the boundary layer behavior.
• Surface condition: Roughness or ice accumulation on the wing's leading edge can disrupt airflow and reduce the stall angle.
• Flaps and slats: High-lift devices increase the lift coefficient at a given angle of attack (https://www.wikiwhat.page/kavramlar/Angle%20of%20Attack) and also increase the stall angle.