Compressible Flow
Air as an ideal gas with k = 1.4 undergoes a normal shock. The upstream conditions are px = 0.5 bar, Tx = 280 K, and Mx = 1.8. Determine
(a) the pressure py, in bar.
(b) the stagnation pressure pox, in bar.
(c) the stagnation temperature Tox, in K.
(d) the change in specific entropy across the shock, in kJ/kg . K.
(e) Plot the quantities of parts (a)–(d) versus Mx ranging from 1.0 to 2.0. All other upstream conditions remain the same.
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