initial commit / add all books

9 files changed, 256 insertions, 0 deletions

diff --git a/2657/CH11/EX11.1/Ex11_1.sce b/2657/CH11/EX11.1/Ex11_1.sce
new file mode 100755
index 000000000..05099bf91
--- /dev/null
+++ b/2657/CH11/EX11.1/Ex11_1.sce
@@ -0,0 +1,28 @@
+//Calculation of the throat diameter

+clc,clear

+//Given:

+m_a=5 //Mass of air in kg/min

+P1=1.013 //Pressure of air in bar

+T1=27+273 //Temperature of air in K

+C1=0,C2=90 //Flow velocity at opening and throat in m/s

+Cv=0.8 //Velocity coefficient

+cp=1.005 //Specific heat at constant pressure in kJ/kgK

+g=1.4 //Specific heat ratio(gamma)

+//Solution:

+//Refer fig 11.32

+//Defining, y as a function of P2

+//This function is the difference of C2 actual and C2 given 

+function [y]=f(P2)

+    C2_act=0.8*sqrt(2*cp*1000*T1*(1-(P2/P1)^((g-1)/g)))

+    y=C2_act-C2

+endfunction

+funcprot(0);

+//The function f is solve for zero to get the value of P2

+P2=fsolve(1,f) //Pressure at throat in bar

+R=0.287 //Specific gas constant in kJ/kgK

+rho1=P1*100/(R*T1) //Mass density at opening in kg/m^3

+rho2=rho1*(P2/P1)^(1/g) //Mass density at throat in kg/m^3

+A2=m_a/(60*rho2*C2) //Cross section area at throat in m^2

+d2=sqrt(4*A2/%pi) //Diameter of cross section in m

+//Results:

+printf("\n The throat diameter of the choke, d2 = %.2f cm\n\n",d2*100)

diff --git a/2657/CH11/EX11.2/Ex11_2.sce b/2657/CH11/EX11.2/Ex11_2.sce
new file mode 100755
index 000000000..5de4e0444
--- /dev/null
+++ b/2657/CH11/EX11.2/Ex11_2.sce
@@ -0,0 +1,34 @@
+//Calculation of throat diameter and orifice diameter

+clc,clear

+//Given:

+m_a=6,m_f=.45 //Mass of air and fuel in kg/min

+rho_f=740 //Density of fuel in kg/m^3

+P1=1.013 //Pressure of air in bar

+T1=27+273 //Temperature of air in K

+C2=92 //Flow velocity at throat in m/s

+Cv=0.8 //Velocity coefficient

+Cd_f=0.60 //Coefficient of discharge of fuel

+cp=1.005 //Specific heat at constant pressure in kJ/kgK

+g=1.4 //Specific heat ratio(gamma)

+//Solution:

+//Defining, y as a function of P2

+//This function is the difference of C2 actual and C2 given 

+function [y]=f(P2)

+    C2_act=Cv*sqrt(2*cp*10^3*T1*(1-(P2/P1)^((g-1)/g)))

+    y=C2_act-C2

+endfunction

+funcprot(0);

+//The function f is solve for zero to get the value of P2

+P2=fsolve(1,f) //Pressure at throat in bar

+R=0.287 //Specific gas constant in kJ/kgK

+rho1=P1*100/(R*T1) //Mass density at opening in kg/m^3

+rho2=rho1*(P2/P1)^(1/g) //Mass density at throat in kg/m^3

+A2=m_a/(60*rho2*C2) //Cross section area at throat in m^2

+d2=sqrt(4*A2/%pi) //Diameter of cross section in m

+deltaP_v=P1-P2 //Pressure drop at venturi in bar

+deltaP_f=0.75*deltaP_v //Given, Pressure drop at fuel metering orifice in bar

+A_f=m_f/(60*Cd_f*sqrt(2*rho_f*deltaP_f*10^5)) //Area of cross section of fuel nozzle in m^2

+d_f=sqrt(4*A_f/%pi) //Diameter of cross section of fuel nozzle in m

+//Results:

+printf("\n The throat diameter of the choke, d2 = %.3f cm",d2*100)

+printf("\n The orifice diameter, d_f = %.2f mm\n\n",d_f*1000)

diff --git a/2657/CH11/EX11.3/Ex11_3.sce b/2657/CH11/EX11.3/Ex11_3.sce
new file mode 100755
index 000000000..e974a1ed5
--- /dev/null
+++ b/2657/CH11/EX11.3/Ex11_3.sce
@@ -0,0 +1,18 @@
+//Calculation of suction at throat

+clc,clear

+//Given:

+d=10,l=12 //Bore and stroke in cm

+n=4 //Number of cylinders

+N=2000 //Speed of engine in rpm

+d2=3 //Diameter of throat in cm

+eta_vol=70 //Volumetric efficiency

+rho_a=1.2 //Density of air in kg/m^3

+Cd_a=0.8 //Coefficient of discharge for air

+//Solution:

+V_s=(%pi/4)*d^2*l*n*10^-6 //Swept volume of engine in m^3

+V_act=eta_vol*V_s*N/(2*100*60) //Actual volume sucked in m^3/s

+m_a=V_act*rho_a //Mass of air sucked in kg/s

+deltaP_v=(m_a*4/(Cd_a*%pi*d2^2*10^-4))^2/(2*rho_a) //Pressure drop at venturi in pascal

+//Results:

+printf("\n The suction at the throat = %.4f bar\n\n",deltaP_v/10^5)

+//Answer in the book is wrong

diff --git a/2657/CH11/EX11.4/Ex11_4.sce b/2657/CH11/EX11.4/Ex11_4.sce
new file mode 100755
index 000000000..e5c872f96
--- /dev/null
+++ b/2657/CH11/EX11.4/Ex11_4.sce
@@ -0,0 +1,23 @@
+//Calculation of the diameter of fuel jet

+clc,clear

+//Given:

+m_f=7.5 //Mass of fuel in kg/hr

+s=0.75 //Specific gravity of the fuel

+T1=25+273 //Temperature of air in K

+A_F=15 //Air fuel ratio

+d=22 //Diameter of choke tube in mm

+z=4 //Elevation of the jet in mm

+Cd_a=0.82,Cd_f=0.7 //Coefficient of discharge for air and fuel

+P1=1.013 //Pressure of air in bar

+g=9.81 //Accelaration due to gravity in m/s^2

+//Solution:

+R=0.287 //Specific gas constant in kJ/kgK

+rho_a=P1*100/(R*T1) //Mass density of air in kg/m^3

+rho_f=s*1000 //Mass density of fuel in kg/m^3

+m_a=A_F*m_f/3600 //Mass of air in kg/s

+deltaP_v=(m_a*4/(Cd_a*%pi*d^2*10^-6))^2/(2*rho_a) //Pressure drop at venturi in pascal

+A_f=m_f/(3600*Cd_f*sqrt(2*rho_f*(deltaP_v-z*10^-3*g*rho_f))) //Area of cross section of fuel nozzle in m^2

+d_f=sqrt(4*A_f/%pi) //Diameter of cross section of fuel nozzle in m

+//Results:

+printf("\n The diameter of the fuel jet of a simple carburettor, d_f = %.3f mm\n\n",d_f*1000)

+//Answer in the book is wrong

diff --git a/2657/CH11/EX11.5/Ex11_5.sce b/2657/CH11/EX11.5/Ex11_5.sce
new file mode 100755
index 000000000..09079d3e0
--- /dev/null
+++ b/2657/CH11/EX11.5/Ex11_5.sce
@@ -0,0 +1,39 @@
+//Calculations on carburettor

+clc,clear

+//Given:

+V_s=1489 //Capacity of the engine in cc

+N=4200 //Speed of the engine in rpm

+eta_v=70 //Volumetric efficiency

+A_F=13 //Air fuel ratio

+C2=90 //Flow velocity at throat in m/s

+Cd_a=0.85,Cd_f=0.66 //Coefficient of discharge for air and fuel

+s=0.74 //Specific gravity of the fuel

+z=6 //Elevation of the jet in mm

+P1=1.013 //Pressure of air in bar

+T1=27+273 //Temperature of air in K

+g=1.4 //Specific heat ratio(gamma)

+cp=1.005 //Specific heat at constant pressure in kJ/kgK

+//Solution:

+V_s=V_s*10^-6 //Swept volume in m^3

+V_act=eta_v*V_s*N/(2*100*60) //Actual volume sucked in m^3/s

+R=0.287 //Specific gas constant in kJ/kgK

+m_a=P1*10^5*V_act/(R*10^3*T1) //Mass of air sucked in kg/s

+//Defining, y as a function of P2

+//This function is the difference of C2 actual and C2 given 

+function [y]=f(P2)

+    C2_act=sqrt(2*cp*10^3*T1*(1-(P2/P1)^((g-1)/g)))

+    y=C2_act-C2

+endfunction

+funcprot(0);

+//The function f is solve for zero to get the value of P2

+P2=fsolve(1,f) //Pressure at throat in bar

+V2=V_act*(P1/P2)^(1/g) //Volume at throat in m^3/s

+A2=V2/(C2*Cd_a) //Cross section area at throat in m^2

+d2=poly(0,'d2') //Defining the diameter of choke as unknown in m

+d_f=d2/2.5 //Given

+d2=roots(%pi/4*(d2^2-d_f^2)-A2) //Diameter of choke in m

+m_f=m_a/A_F //Mass of fuel sucked in kg/s

+A_f=m_f/(Cd_f*sqrt(2*s*1000*(P1*10^5-P2*10^5-z*10^-3*9.81*s*1000))) //Area of cross section of fuel nozzle in m^2

+d_f=sqrt(4*A_f/%pi) //Diameter of cross section of fuel nozzle in m

+//Results:

+printf("\n The diameter of the fuel jet of a simple carburettor, D_jet = %.2f mm\n\n",d_f*1000)

diff --git a/2657/CH11/EX11.6/Ex11_6.sce b/2657/CH11/EX11.6/Ex11_6.sce
new file mode 100755
index 000000000..4efadc5cd
--- /dev/null
+++ b/2657/CH11/EX11.6/Ex11_6.sce
@@ -0,0 +1,42 @@
+//Calculations on carburettor

+clc,clear

+//Given:

+V_s=1710 //Capacity of the engine in cc

+N=5400 //Speed of the engine in rpm

+eta_vol=70 //Volumetric efficiency

+n=2 //Number of carburettor

+A_F=13 //Air fuel ratio

+C2=107 //Flow velocity at throat in m/s

+Cd_a=0.85,Cd_f=0.66 //Coefficient of discharge for air and fuel

+s=0.75 //Specific gravity of the fuel

+z=6 //Elevation of the jet in mm

+P1=1.013 //Pressure of air in bar

+T1=27+273 //Temperature of air in K

+g=1.4 //Specific heat ratio(gamma)

+cp=1.005 //Specific heat at constant pressure in kJ/kgK

+//Solution:

+V_s=V_s*10^-6 //Swept volume in m^3

+V_act=eta_vol*V_s*N/(2*100*60) //Actual volume sucked in m^3/s

+V_act=V_act/n //Actual volume of air sucked through each carburettor in m^3/s

+R=0.287 //Specific gas constant in kJ/kgK

+m_a=P1*10^5*V_act/(R*10^3*T1) //Mass of air sucked in kg/s

+//Defining, y as a function of P2

+//This function is the difference of C2 actual and C2 given

+function [y]=f(P2)

+    C2_act=sqrt(2*cp*10^3*T1*(1-(P2/P1)^((g-1)/g)))

+    y=C2_act-C2

+endfunction

+funcprot(0);

+//The function f is solve for zero to get the value of P2

+P2=fsolve(1,f) //Pressure at throat in bar

+V2=V_act*(P1/P2)^(1/g) //Volume at throat in m^3/s

+A2=V2/(C2*Cd_a) //Cross section area at throat in m^2

+d2=poly(0,'d2') //Defining the diameter of choke as unknown in m

+d_f=d2/2.5 //Given

+d2=roots(%pi/4*(d2^2-d_f^2)-A2) //Diameter of choke in m

+m_f=m_a/A_F //Mass of fuel sucked in kg/s

+A_f=m_f/(Cd_f*sqrt(2*s*1000*(P1*10^5-P2*10^5-z*10^-3*9.81*s*1000))) //Area of cross section of fuel nozzle in m^2

+d_f=sqrt(4*A_f/%pi) //Diameter of cross section of fuel nozzle in m

+//Results:

+printf("\n The diameter of the choke tube, D = %.2f cm",d2(1)*100)

+printf("\n The diameter of the fuel jet of a simple carburettor, D_f = %.2f mm\n\n",d_f*1000)

diff --git a/2657/CH11/EX11.7/Ex11_7.sce b/2657/CH11/EX11.7/Ex11_7.sce
new file mode 100755
index 000000000..256945ec3
--- /dev/null
+++ b/2657/CH11/EX11.7/Ex11_7.sce
@@ -0,0 +1,24 @@
+//Change in air fuel ratio at altitude

+clc,clear

+//Given:

+ha=5000 //Altitude in m

+A_F=14 //Air fuel ratio at sea level

+P1=1.013 //Pressure of air in bar at sea level

+T1=27+273 //Temperature of air in K at sea level

+R=0.287 //Specific gas constant in kJ/kgK

+function t=f1(h),t=ts-0.0065*h,endfunction //Temperature(t in degreeC) as a function of altitude(h in m) 

+function h=f2(P),h=19200*log10(1.013/P),endfunction //Altitude(h in m) as a function of pressure(P in bar)

+//Solution:

+ts=T1-273 //Sea level temperature in degreeC

+T2=f1(ha) //Temperature at altitude(ha = 5000 m) in degreeC

+T2=T2+273 //in K

+//Defining, y as a function of P

+//This function is the difference of function(f2) and ha given

+function y=f(P),y=f2(P)-ha,endfunction

+//The function f is solve for zero to get the value of P2

+P2=fsolve(1,f) //Pressure at altitude(ha = 5000 m) in bar

+rho_a=P2/(R*T2) //Density of air at altitude in kg/m^3

+rho_s=P1/(R*T1) //Density of air at sea level in kg/m^3

+A_F_a=A_F*sqrt(rho_a/rho_s) //Air fuel ratio at altitude

+//Results:

+printf("\n The air fuel ratio supplied at 5000 m altitude by a carburettor = %.2f\n\n",A_F_a)

diff --git a/2657/CH11/EX11.8/Ex11_8.sce b/2657/CH11/EX11.8/Ex11_8.sce
new file mode 100755
index 000000000..ba3da9fee
--- /dev/null
+++ b/2657/CH11/EX11.8/Ex11_8.sce
@@ -0,0 +1,26 @@
+//Calculation of air fuel ratio

+clc,clear

+//Given:

+d2=20,d_f=1.25 //Diameter of throat and fuel nozzle in mm

+Cd_a=0.85,Cd_f=0.66 //Coefficient of discharge for air and fuel

+z=5 //Elevation of the jet in mm

+rho_a=1.2,rho_f=750 //Mass density of air and fuel in kg/m^3

+deltaP_a=0.07 //Pressure drop of air in bar

+g=9.806 //Accelaration due to gravity in m/s^2

+//Solution:

+//(a)Nozzle lip is neglected

+A_f=(%pi/4)*d_f^2,A2=(%pi/4)*d2^2 //Area of cross section of fuel nozzle and venturi in mm^2

+m_a1=Cd_a*A2*sqrt(2*rho_a*deltaP_a),m_f1=Cd_f*A_f*sqrt(2*rho_f*deltaP_a) //Air flow and fuel flow

+A_F1=m_a1/m_f1 //Air fuel ratio

+//(b)Nozzle lip is taken into account

+m_a2=m_a1 //Air flow remain same

+m_f2=Cd_f*A_f*sqrt(2*rho_f*(deltaP_a-z*10^-3*g*rho_f*10^-5)) //Fuel flow

+A_F2=m_a2/m_f2 //Air fuel ratio

+//(c)Minimum velocity required to start the fuel flow when nozzle lip is provided

+//To just start the fuel flow pressure difference in venturi must be equivalent to the nozzle lip pressure

+deltaP_a=z*10^-3*g*rho_f //Pressure difference in N/m^2

+C2=sqrt(2*deltaP_a/rho_a) //Minimum velocity of air at throat in m/s

+//Results:

+printf("\n The air fuel ratio when the nozzle lip is neglected = %.1f",A_F1)

+printf("\n The air fuel ratio when the nozzle lip is taken into account = %.3f",A_F2)

+printf("\n The minimum velocity required to start the fuel flow when lip is provided = %.2f m/s",C2)

diff --git a/2657/CH11/EX11.9/Ex11_9.sce b/2657/CH11/EX11.9/Ex11_9.sce
new file mode 100755
index 000000000..6b62a60b5
--- /dev/null
+++ b/2657/CH11/EX11.9/Ex11_9.sce
@@ -0,0 +1,22 @@
+//Effect of air cleaner

+clc,clear

+//Given:

+A_F=14 //Air fuel ratio at sea level

+P2=0.834 //Pressure at venturi throat without an air cleaner in bar

+P1=1.013 //Pressure of air in bar at sea level

+deltaP_ac=30 //Pressure drop to air cleaner in mm of mercury

+m_a=250 //Air flow in kg/hr

+//Solution:

+//No air cleaner

+deltaP_a1=P1-P2 //Pressure difference at venturi throat in bar

+//When air cleaner is fitted

+deltaP_ac=deltaP_ac/750 //Pressure drop to air cleaner in bar

+p=poly(0,'p') //Defining pressure at venturi throat with an air cleaner as unknown in bar

+deltaP_a2=P1-deltaP_ac-p //Pressure difference at venturi throat in bar

+//For same air flow and constant coefficients pressure difference in above two cases is same

+p=roots(deltaP_a2-deltaP_a1) //Pressure at venturi throat with an air cleaner in bar

+deltaP_f=P1-p //Pressure difference at venturi throat when air cleaner is fitted in bar

+A_F_f=A_F*sqrt(deltaP_a1/deltaP_f) //Air fuel ratio when air cleaner is fitted

+//Results:

+printf("\n (a)The throat pressure when the air cleaner is fitted, P = %.3f bar",p)

+printf("\n (b)Air fuel ratio with air cleaner is fitted = %.2f\n\n",A_F_f)