Gas Dynamics (Compressible Flow) Normal Shock Wave

AI Thread Summary
The discussion revolves around calculating the changes in pressure, temperature, stagnation pressure, and velocity caused by a blast wave traveling at 60,000 m/s in air under standard atmospheric conditions. The user attempts to apply the equation v = M * sqrt(gamma * R * T) but encounters confusion, resulting in an incorrect Mach number of 180. The speed of sound in air is approximately 340 m/s, indicating that the wave is significantly supersonic. Participants discuss the importance of using isentropic and Normal Shock Wave tables for accurate calculations. The conversation emphasizes the complexities involved in analyzing compressible flow and shock wave dynamics.
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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.
 
Physics news on Phys.org
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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