From 7f60ea012dd2524dae921a2a35adbf7ef21f2bb6 Mon Sep 17 00:00:00 2001
From: prashantsinalkar
Date: Tue, 10 Oct 2017 12:27:19 +0530
Subject: initial commit / add all books

---
 3765/CH5/EX5.4/Ex5_4.sce | 27 +++++++++++++++++++++++++++
 1 file changed, 27 insertions(+)
 create mode 100644 3765/CH5/EX5.4/Ex5_4.sce

(limited to '3765/CH5/EX5.4/Ex5_4.sce')

diff --git a/3765/CH5/EX5.4/Ex5_4.sce b/3765/CH5/EX5.4/Ex5_4.sce
new file mode 100644
index 000000000..4a06cf437
--- /dev/null
+++ b/3765/CH5/EX5.4/Ex5_4.sce
@@ -0,0 +1,27 @@
+clc
+// Example 5.4.py
+// Consider the flow through a convergent-divergent duct with an exit to throat area
+// ratio of 2. The reservoir pressure is 1 atm, and the exit pressure is 0.95 atm.
+// Calculate the mach numbers at the throat and at the exit.
+
+// Variable declaration
+po = 1.0           // reservoir pressure (in atm)
+pe = 0.95          // pressure at the exit (in atm)
+Ae_by_At = 2.0  // ratio of exit to throat area
+
+// Calculations
+// from table A1 for po/pe = 1.053
+Me = 0.28           // mach number at exit
+Ae_by_Astar = 2.17  // nearest entry
+
+At_by_Astar = 1 / Ae_by_At * Ae_by_Astar // At/Astar = At/Ae * Ae/Astar
+
+// from table A1 for At/A* = 1.085
+Mt = 0.72           // mach number at throat
+
+
+// Results 
+printf("\n Mach number at exit %.2f", Me)
+
+printf("\n Mach number at throat %.2f", Mt)
+
-- 
cgit