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-rw-r--r--629/CH12/EX12.2/ex12_2.txt3
-rw-r--r--629/CH12/EX12.2/example12_2.sce16
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diff --git a/629/CH12/EX12.2/ex12_2.txt b/629/CH12/EX12.2/ex12_2.txt
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+
+ The Mach number of the aircraft, M = 1.58.
+ \ No newline at end of file
diff --git a/629/CH12/EX12.2/example12_2.sce b/629/CH12/EX12.2/example12_2.sce
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+clear
+clc
+//Example 12.2 MACH-NUMBER CALCULATION
+z=13; //[km]
+alpha=5.87; //[K/km]
+To=296; //[K]
+//Temperature at z
+T=To-alpha*z //[K]
+R=287; //[J/Kg.K]
+k=1.4;
+//Speed of sound
+c=sqrt(k*R*T) //[m/s]
+V=470; //speed of fighter[m/s]
+//Mach number
+M=V/c
+printf("\n The Mach number of the aircraft, M = %.2f.\n",M) \ No newline at end of file