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

---
 3685/CH21/EX21.4/Ex21_4.sce | 54 +++++++++++++++++++++++++++++++++++++++++++++
 3685/CH21/EX21.4/Ex21_4.txt |  5 +++++
 2 files changed, 59 insertions(+)
 create mode 100644 3685/CH21/EX21.4/Ex21_4.sce
 create mode 100644 3685/CH21/EX21.4/Ex21_4.txt

(limited to '3685/CH21/EX21.4')

diff --git a/3685/CH21/EX21.4/Ex21_4.sce b/3685/CH21/EX21.4/Ex21_4.sce
new file mode 100644
index 000000000..a560bdd2a
--- /dev/null
+++ b/3685/CH21/EX21.4/Ex21_4.sce
@@ -0,0 +1,54 @@
+clc
+// Given that
+v = 800 // Speed of aircraft in km/h
+h = 10700 // Height of aircraft in m
+p0 = 0.24 // Pressure in bar
+t0 = -50 // Temperature in degree centigrade
+r_p = 10 // Compressor pressure ratio
+t03 = 1093 // Max cycle temperature in K
+n_ed = 0.9 // Entry duct efficiency
+n_c = 0.9 // Isentropic efficiency of compressure
+p_ = 0.14 // Stagnation pressure loss in combustion chamber in bar
+cv = 43.3 // Calorific value of fuel in MJ/kg
+n_C = 0.98 // Combustion efficiency
+n_t = 0.92 // Isentropic efficiency of turbine
+n_m = 0.98 // Mechanical efficiency of drive
+n_j = 0.92 // Jet pipe efficiency
+a = 0.08 // Nozzle outlet area in m^2
+Cp = 1.005 // Heat capacity of air in kJ/kgK
+gama = 1.4 // Ratio of heat capacities for air
+Cp_ = 1.15 // Heat capacity for gases in kJ/kgK
+gama_ = 1.333 // Ratio of heat capacities for gases
+printf("\n Example 21.4\n")
+KE = (1/2)*(v*5/18)^2
+tr = KE/(1000*Cp)
+t01 = tr + (273+t0)
+t01_s = (t0+273)+(n_ed*(t01-(t0+273)))
+p01 = p0*((t01_s/(t0+273))^(gama/(gama-1)))
+t02_s = t01*((r_p)^((gama-1)/gama))
+t02 = (t01) + (t02_s-t01)/n_c
+p02 = p01*r_p
+p03 = p02-p_
+t04 = t03 - (Cp*(t02-t01)/(Cp_*n_m))
+t04_s = t03-(t03-t04)/n_t
+p04 = p03/((t03/t04_s)^(gama_/(gama_-1)))
+p_cr = p04*((2/(gama_+1))^(gama_/(gama_-1)))
+t05 = t04*(2/(gama_+1))
+t05_s = t04-((t04-t05)/n_j)
+p05 = p04/((t04/t05_s)^(gama_/(gama_-1)))
+R = Cp_*(gama_-1)/gama_
+v5 = R*t05/(p05*100)
+Vj = sqrt(gama_*R*1000*t05)
+m = a*Vj/v5
+Mt = m*(Vj-v*(5/18))
+Pt = (p05-p0)*a*10^5
+Tt = Mt+Pt
+Q1 = m*(t03-t02)*Cp_
+m_f = Q1/(cv*1000*n_C)
+m_sf = m_f*1000/Tt
+printf("\n Total thrust developed = %f N,\n The specific fuel consumption = %f kg/kNs",Tt,m_sf)
+// The answers given in the book contain round off error.
+
+
+
+
diff --git a/3685/CH21/EX21.4/Ex21_4.txt b/3685/CH21/EX21.4/Ex21_4.txt
new file mode 100644
index 000000000..6f68d33cf
--- /dev/null
+++ b/3685/CH21/EX21.4/Ex21_4.txt
@@ -0,0 +1,5 @@
+ 
+ Example 21.4
+
+ Total thrust developed = 6346.439922 N,
+ The specific fuel consumption = 0.029294 kg/kNs 
\ No newline at end of file
-- 
cgit