🔍 Key Concepts

• Compressor stall in gas turbines is closely related to the angle of attack of the air on the compressor blades • Think about what happens if air hits an airfoil (like a wing or blade) at too great an angle versus too shallow an angle • Distinguish between what happens in the compressor section versus the turbine section of a gas turbine engine

💭 Think About

• Which answer choices refer specifically to compressor rotor blades and which refer to other parts of the engine (like turbine blades or foils)? • How does changing the angle at which air strikes a rotor blade affect whether the airflow stays smooth (laminar) or becomes separated/stalled? • In aerodynamics, when does an airfoil usually stall: when its angle of attack is too low, or when it becomes too high and the airflow separates?

✅ Before You Answer

• Make sure the option you choose mentions the compressor (not turbine or general foil section) • Confirm that your choice involves an angle of attack problem that would cause air to separate from the blade surface • Verify whether stall is typically associated with an angle being too high or too low in basic airfoil theory