Question: Consider a flat plate at an angle of attack a to a Mach 2.4 airflow at 1atm pressure. What is the maximum pressure that can

Consider a flat plate at an angle of attack a to a Mach 2.4 airflow at 1atm pressure. What is the maximum pressure that can occur on the plate surface and still have an attached shock wave at the leading edge? At what value of a does this occur?

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