A re-entry module flies with Mach 10 at an ambient temperature of –27°C with. CP = 840 J/kg-K, gas constant R = 140 J/kg-K. What is the stagnation temperature at the tip of the nose of the re-entry module?

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    $\begingroup$ Homework problem? $\endgroup$ – Organic Marble Apr 6 '18 at 14:31
  • $\begingroup$ @uhoh I don't believe that answer is relevant at all to this question. Before you edited it this was a simple gas thermodynamics 101 homework problem. Note that heating does not enter into it, and the 're-entry module' part is irrelevant, it could be any M 10 flow./ $\endgroup$ – Organic Marble Apr 7 '18 at 12:24
  • $\begingroup$ @OrganicMarble rolled-back. I had thought that homework problems were off-topic. I'm surprised to hear that heating does not enter into a question about temperature at the tip of a nosecone during reentry, so I'll wait for the answer to find out! $\endgroup$ – uhoh Apr 7 '18 at 12:48
  • $\begingroup$ Check the mach number form of the equation here. en.wikipedia.org/wiki/Stagnation_temperature $\endgroup$ – Organic Marble Apr 7 '18 at 12:52
  • $\begingroup$ Thank you, everyone, for your comments. The "Re-entry module" part is indeed irrelevant and I've realized that after going through the question properly. I basically got panicked as I don't have much idea about the reentry module.I have solved the question using the relation between Stagnation Temperature and Mach number. $\endgroup$ – alamtania Apr 11 '18 at 6:22


Here's how I solved the question. Please ignore the (c) at the end of the solution.

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    $\begingroup$ Good work on this. The caveat to this, of course, is that in a real-life application, the ideal gas assumptions used to derive these equations will break down at Mach numbers and temperatures that high. The resulting temperature of a real gas with those thermodynamic properties at 300-ish K would be lower than this. $\endgroup$ – Tristan Apr 13 '18 at 16:13

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