Gas Dynamics (Compressible Flow) Normal Shock Wave

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SUMMARY

The discussion focuses on calculating the changes in pressure, temperature, stagnation pressure, and velocity caused by a normal shock wave traveling through air at 60,000 m/s. The relevant equation used is v = M * sqrt(gamma * R * T), where the initial conditions are set at a pressure of 103.5 kPa and a temperature of 298 K. The attempt at a solution indicates a Mach number (M) of 180, which is deemed incorrect given the context of the problem. The shock wave's speed significantly exceeds the speed of sound in air, which is approximately 340 m/s.

PREREQUISITES
  • Understanding of compressible flow dynamics
  • Familiarity with normal shock wave tables
  • Knowledge of isentropic relationships in gas dynamics
  • Proficiency in using the equation v = M * sqrt(gamma * R * T)
NEXT STEPS
  • Study the derivation and application of normal shock wave equations
  • Learn how to interpret isentropic tables for air
  • Research the effects of shock waves on pressure and temperature in compressible flows
  • Explore advanced topics in gas dynamics, such as oblique shock waves
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Homework Statement



Suppose that a blast wave, which might have been initiated by an atomic bomb explosion, is traveling through air at standard atmospheric conditions with a speed of 60,000 m/s
find change in ( pressure , temperature , stagnation pressure , velocity ) produced by the wave with respect to an observer who is stationary with respect to the undisturbed air.


Homework Equations



v= M*sqrt(gamma*R*T)

isentropic tables & Normal Shock Wave Tables.

The Attempt at a Solution



i'm trying to use the equation v=M sqrt(gamma*R*T) with air p=103.5 kpa , T=298K , but i can't seem to understand the problem , since i get M=180 which is obviously wrong.
 
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The shock wave is traveling at 60000 m/s, and the speed of sound is approx. 340 m/s.
M = 180 is about right.
 

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