Question: Consider a flat plate at an angle of attack ( alpha ) to a Mach 2 . 4 airflow at 1 atm

Consider a flat plate at an angle of attack

\ (\

alpha

\)

to a Mach

2.4

airflow at

1

atm 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

\ (\

alpha

\)

does this occur?

$Consider a flat plate at an angle of attack \ ( \$

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