1. A fixed-geometry supersonic inlet starts at a Mach number of 3. After starting, the cruise Mach number is 2, and the operatin
g shock is positioned at a location where the area is 10% larger than the throat. a) Assuming the flow is ideal except for shock losses, find the inlet stagnation pressure ratio poz/poa during cruise. b) During cruise, the Mach number at the exit of the diffuser M, is required to be 0.3. Determine the ratio of the areas at the diffuser exit to that at the inlet (find A/A), and the static pressure ratio pz/p.
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Answer: 37.4K
Explanation:
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Answer: ε₁+ε₂+ε₃ = 0
Explanation: Considering the initial and final volume to be constant which gives rise to the relation:-
l₀l₀l₀=l₁l₂l₃
taking natural log on both sides
Considering the logarithmic Laws of division and multiplication :
ln(AB) = ln(A)+ln(B)
ln(A/B) = ln(A)-ln(B)
Use the image attached to see the definition of true strain defined as
ln(l1/1o)= ε₁
which then proves that ε₁+ε₂+ε₃ = 0
