Consider the purely subsonic flow in a convergent-divergent duct. The inlet, throat, and exit area are (1.00
Question:
Consider the purely subsonic flow in a convergent-divergent duct. The inlet, throat, and exit area are \(1.00 \mathrm{~m}^{2}, 0.70 \mathrm{~m}^{2}\), and \(0.85 \mathrm{~m}^{2}\), respectively. If the inlet Mach number and pressure are 0.3 and \(0.8 \times 10^{5} \mathrm{~N} / \mathrm{M}^{2}\), respectively, calculate:
a. \(M\) and \(p\) at the throat
b. \( M\) and \(p\) at the exit
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Step by Step Answer:
To calculate the Mach number and pressure at the throat and exit of a convergentdivergent duct we can use the areaMach number relation and the isentropic flow equations Lets proceed with the calculati...View the full answer
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