initial commit / add all books

6 files changed, 144 insertions, 0 deletions

diff --git a/3720/CH11/EX11.1/Ex11_1.sce b/3720/CH11/EX11.1/Ex11_1.sce
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index 000000000..80133157d
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+++ b/3720/CH11/EX11.1/Ex11_1.sce
@@ -0,0 +1,14 @@
+//Example 11_1

+clc;clear;funcprot(0);

+//Properties

+rho=0.07489;//The density of air in lbm/ft^3

+//Given values

+P_atm=1;// atm

+T=70;// F

+F_d=68;// Force in lbf

+V=60*1.467;// ft/s^2

+A=22.26;// ft^2

+

+//Calculation

+C_d=(2*F_d*(32.2))/(rho*A*V^2);//The drag coefficient of the car

+printf('The drag coefficient of the car ,C_d=%0.2f \n',C_d);

diff --git a/3720/CH11/EX11.2/Ex11_2.sce b/3720/CH11/EX11.2/Ex11_2.sce
new file mode 100644
index 000000000..4d5986734
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+++ b/3720/CH11/EX11.2/Ex11_2.sce
@@ -0,0 +1,30 @@
+//Example 11_2

+clc;clear;funcprot(0);

+//Properties

+rho_a=1.20;// The density of air in kg/m^3

+rho_g=.8;//The density of gasoline in kg /L

+n_o=0.3;// The over all efficiency of the engine 

+C_dc=1.1;// The drag coefficient for a circular disk

+C_dh=0.4;//The drag coefficient for a hemispherical body

+HV=44000;// The heating value of gasoline in kJ/kg

+

+// Given values

+V=95;// km/h

+Pr=0.60;//Price of gasoline in $/L

+D=0.13;// m

+L=24000;// km/year

+

+//Calculation

+A=(%pi*0.13^2)/4;//m^2

+F_d=(C_dc*A*rho_a*V^2)/(2*3.6^2);//The drag force acting on the flat mirror in N

+W_drag=F_d*L;// kJ/year

+E_in=W_drag/n_o;// kJ/year

+m_f=E_in/HV; // kg/year

+Amount=m_f/rho_g;// L/year

+Cost=(Amount*Pr);// $/year

+Rr=(C_dc-C_dh)/C_dc;// Reduction ratio

+Fr=Rr*Amount;// Fuel reduction in L/year

+printf('Fuel reduction =%0.2f L/year\n',Fr);

+Cr=Rr*Cost;// Cost reduction in $/year

+printf('Cost reduction =%0.2f $/year\n',Cr);

+// The answer vary due to round off error

diff --git a/3720/CH11/EX11.3/Ex11_3.sce b/3720/CH11/EX11.3/Ex11_3.sce
new file mode 100644
index 000000000..9a2371dac
--- /dev/null
+++ b/3720/CH11/EX11.3/Ex11_3.sce
@@ -0,0 +1,18 @@
+//Example 11_3

+clc;clear;funcprot(0);

+//Assumptions

+Re_cr=5*10^5;

+//Properties

+rho=876;//The density of engine oil at 40°C kg/m^3

+nu=2.485*10^-4;//m^2/s

+//Given values

+V=2;// Free stream velocity in m/s

+L=5;// m

+b=1;//m

+

+//Calculation

+Re_L=(V*L)/nu;// The Reynolds number at the end of the plate

+C_f=1.328*Re_L^(-0.5);// The average friction coefficient

+A=L*b;// m^2

+F_d=C_f*A*rho*(V^2/2);// N

+printf('The drag force,F_d =%0.0f N\n',F_d);

diff --git a/3720/CH11/EX11.4/Ex11_4.sce b/3720/CH11/EX11.4/Ex11_4.sce
new file mode 100644
index 000000000..38be355b8
--- /dev/null
+++ b/3720/CH11/EX11.4/Ex11_4.sce
@@ -0,0 +1,18 @@
+//Example 11_4

+clc;clear;funcprot(0);

+//Properties

+rho=999.1;//kg/m^3

+mu=1.138*10^-3;// kg/m.s

+//Given values

+D=0.022;// m

+V=4;// m/s

+L=30;// m

+A=L*D;// m^2

+

+//Calculation

+Re=(rho*V*D)/mu;

+//The drag coefficient corresponding to the value Re from Fig. 11–34

+C_d=1;

+F_d=C_d*A*rho*(V^2/2);

+printf('The drag force acting on the pipe,F_d =%0.0f N\n',F_d);

+disp('The drag force acting on the pipe,F_d ~=5300 N');

diff --git a/3720/CH11/EX11.5/Ex11_5.sce b/3720/CH11/EX11.5/Ex11_5.sce
new file mode 100644
index 000000000..61c10d76d
--- /dev/null
+++ b/3720/CH11/EX11.5/Ex11_5.sce
@@ -0,0 +1,36 @@
+//Example 11_5

+clc;clear;

+//Properties

+rho_ag=1.20;// kg/m^3

+rho_ac=0.312;// kg/m^3

+C_Lmax1=1.52;// The maximum lift coefficient of the wing with flaps

+C_Lmax2=3.48;// The maximum lift coefficient of the wing without flaps

+//Given values

+m=70000;// kg

+A=150;// m^2

+V=558;/// km/h

+g=9.81;// m/s^2

+

+// Calculation

+//(a)

+W=m*g;// N

+V=V/3.6;// m/s

+V_min1=sqrt((2*W)/(rho_ag*C_Lmax1*A));// m/s

+V_min2=sqrt((2*W)/(rho_ag*C_Lmax2*A));// m/s

+V_1s=1.2*V_min1*3.6;// 1 m/s=3.6 km/h

+printf('(a)Without flaps:V_min1,safe =%0.0f km/h\n',V_1s);

+V_2s=1.2*V_min2*3.6;// 1 m/s=3.6 km/h

+printf('    With flaps:V_min2,safe =%0.0f km/h\n',V_2s);

+//(b)

+F_l=W;// N

+C_l=F_l/(1/2*rho_ac*V^2*A);// The lift coefficient

+//For the case with no flaps, the angle of attack corresponding to this value of C_L is determined from Fig. 11–45 to be

+alpha=10;// The angle of attack in degree

+printf('(b)The angle of attack,alpha~=%0.0f degree\n',alpha);

+//(c)

+// From Fig.11-45,C_d~=0.03

+C_d=0.03;// The drag coefficient

+F_d=(C_d*A*rho_ac*(V^2/2))/1000;//kN

+P=F_d*V;// kW

+printf('(c)The power that needs to be supplied to provide enough thrust to overcome wing drag,P=%0.0f kW\n',P);

+// The answer vary due to round off error

diff --git a/3720/CH11/EX11.6/Ex11_6.sce b/3720/CH11/EX11.6/Ex11_6.sce
new file mode 100644
index 000000000..00e7db569
--- /dev/null
+++ b/3720/CH11/EX11.6/Ex11_6.sce
@@ -0,0 +1,28 @@
+//Example 11_6

+clc;clear;funcprot(0);

+//Properties

+rho=0.07350;// lbm/ft^3

+nu=1.697*10^-4;// ft^2/s

+//Given values

+m=0.125;//lbm

+D=2.52;// in

+V=45;// mi/h

+n=4800;// rpm

+P=1;// atm

+T=80;// degree F

+g=9.81;// m/s^2

+

+//Calculation

+V=(45*5280)/3600;// ft/s

+omega=(2*%pi*n)/60;// rad/s

+C=(omega*D)/(2*V);//rad

+//From Fig. 11–53, the lift coefficient corresponding to C

+C_l=0.21;

+A=(%pi*D^2)/4;// ft^2

+F_l=(C_l*A*rho*V^2)/(2*32.2);// lbf

+W=(m*g)/32.2;// lbf

+if(W<=0.125)

+    printf('drop')

+else

+    printf('Wrong')

+end