Discussion
Consider the following statements about inlets:
1. Pressure recovery compares total pressure at the fan face with the free stream.
2. Spillage drag arises when the engine swallows less than the inlet captures.
3. A pitot inlet is adequate for flight at Mach 2.5.
Which of the statements given above is or are correct?
Answer: C
Correct answer: 1 and 2 only
Statement 1 is correct: pressure recovery is total pressure at the fan face over free stream total pressure. Statement 2 is correct: spillage drag arises when the engine swallows less than the inlet captures, the excess spilling around the cowl lip.
Statement 3 is false. A pitot inlet decelerates the flow through a single normal shock, and at Mach 2.5 that shock destroys around half the total pressure. Supersonic flight requires a system of weaker oblique shocks with variable geometry to position them.
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