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Chapter 3: Some Fundamental Aspects of Compressible Flow


Problem 3.5:

An airplane is traveling at km/h at an altitude where the temperature is oC. What is the Mach at which the airplane is flying?

Solution:

Given:
\( V = \) 1500 km/h = 1500/3.6 m/s,
\( T = \)-60oC = 213 K.

To calculate: \( M=? \)

The problem description is schematically shown in Fig. 1.
Fig. 1: Schematic of the problem description

The Mach number can be calculated using the equation,

\[ M=\frac{V}{a}=\frac{V}{\sqrt{\gamma\,R\,T}}=\frac{1500/3.6}{\sqrt{1.4\times287\times213}} \]
\[ \boxed{M=1.42}\ . \]


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