Final answer:
The effects of a flat plate at an angle of attack in a Mach 2.4 airflow include the formation of shock waves and could also see a B. decrease in lift force.
Step-by-step explanation:
The question being asked relates to a flat plate at an angle of attack in a Mach 2.4 airflow and is seeking to understand the potential effects this scenario would have. The applicable effects to consider for a flat plate at an angle in such high-speed airflow include formation of shock waves, as with all supersonic flows encountering an obstruction, and a potential decrease in lift force depending on the specific angle of attack and shape of the airfoil. Because of the complexities involved with compressible flow at these speeds, phenomena such as temperature changes due to compression in shock waves and changes in airfoil performance will occur.
Regarding the speed of air necessary to create lift, Bernoulli's principle can be referenced for a basic understanding, though at high speeds, especially at supersonic speeds, this principle gives only an approximate answer due to factors like turbulence and airflow compressibility. The exact speeds and performance characteristics would require a more in-depth aerodynamic analysis, considering things like altitude, air density changes, and unique aircraft geometry.