initial commit / add all books

13 files changed, 280 insertions, 0 deletions

diff --git a/494/CH8/EX8.1/8_1.sce b/494/CH8/EX8.1/8_1.sce
new file mode 100755
index 000000000..b29ab05eb
--- /dev/null
+++ b/494/CH8/EX8.1/8_1.sce
@@ -0,0 +1,38 @@
+//All the quantities are expressed in SI units

+

+R = 287;

+gam = 1.4;

+V_inf = 250;

+

+//(a)

+//At sea level

+T_inf = 288;

+

+//the velocity of sound is given by

+a_inf = sqrt(gam*R*T_inf);

+

+//thus the mach number can be calculated as

+M_inf = V_inf/a_inf;

+

+printf("\n(a)\nThe Mach number at sea level is:\n        M_inf = %1.3f\n",M_inf)

+

+//similarly for (b) and (c)

+//(b)

+//at 5km

+T_inf = 255.7;

+

+a_inf = sqrt(gam*R*T_inf);

+

+M_inf = V_inf/a_inf;

+

+printf("\n(b)\nThe Mach number at 5 km is:\n        M_inf = %1.2f\n",M_inf)

+

+//(c)

+//at 10km

+T_inf = 223.3;

+

+a_inf = sqrt(gam*R*T_inf);

+

+M_inf = V_inf/a_inf;

+

+printf("\n(c)\nThe Mach number at 10 km is:\n        M_inf = %1.3f\n",M_inf)
\ No newline at end of file
diff --git a/494/CH8/EX8.10/8_10.sce b/494/CH8/EX8.10/8_10.sce
new file mode 100755
index 000000000..c09469861
--- /dev/null
+++ b/494/CH8/EX8.10/8_10.sce
@@ -0,0 +1,25 @@
+//All the quantities are expressed in SI units

+

+M_inf = 2;                     //freestream mach number

+p_inf = 2.65e4;                //freestream pressure

+T_inf = 223.3;                 //freestream temperature

+

+//from Appendix A, for M = 2

+p0_inf = 7.824*p_inf;          //freestream total pressure

+T0_inf = 1.8*T_inf;            //freestream total temperature

+

+//from Appendix B, for M = 2

+p0_1 = 0.7209*p0_inf;          //total pressure downstream of the shock

+T0_1 = T0_inf;                 //total temperature accross the shock is conserved

+

+//since the flow downstream of the shock is isentropic

+p0_2 = p0_1;

+T0_2 = T0_1;

+

+//from Appendix A, for M = 0.2 at point 2

+p2 = p0_2/1.028;

+T2 = T0_2/1.008;

+

+p2_atm = p2/102000;

+

+printf("\nRESULTS\n---------\nThe pressure at point 2 is:\n        p2 = %1.2f atm\n",p2_atm)
\ No newline at end of file
diff --git a/494/CH8/EX8.11/8_11.sce b/494/CH8/EX8.11/8_11.sce
new file mode 100755
index 000000000..ad6ae69c3
--- /dev/null
+++ b/494/CH8/EX8.11/8_11.sce
@@ -0,0 +1,26 @@
+//All the quantities are expressed in SI units

+

+M_inf = 10;                    //freestream mach number

+p_inf = 2.65e4;                //freestream pressure

+T_inf = 223.3;                 //freestream temperature

+

+//from Appendix A, for M = 2

+p0_inf = 0.4244e5*p_inf;       //freestream total pressure

+T0_inf = 21*T_inf;             //freestream total temperature

+

+//from Appendix B, for M = 2

+p0_1 = 0.003045*p0_inf;        //total pressure downstream of shock

+T0_1 = T0_inf;                 //total temperature downstream of shock is conserved

+

+//since the flow downstream of the shock is isentropic

+p0_2 = p0_1;

+T0_2 = T0_1;

+

+//from Appendix A, for M = 0.2 at point 2

+p2 = p0_2/1.028;

+T2 = T0_2/1.008;

+

+p2_atm = p2/102000;

+

+

+printf("\nRESULTS\n---------\nThe pressure at point 2 is:\n        p2 = %2.1f atm\n",p2_atm)
\ No newline at end of file
diff --git a/494/CH8/EX8.13/8_13.sce b/494/CH8/EX8.13/8_13.sce
new file mode 100755
index 000000000..3d49c216e
--- /dev/null
+++ b/494/CH8/EX8.13/8_13.sce
@@ -0,0 +1,12 @@
+//All the quantities are expressed in SI units

+

+p1 = 4.66e4;                                //ambient pressure

+M = 8;                                      //mach number

+

+//from Appendix B, for M = 8

+p0_2 = 82.87*p1;                            //total pressure downstream of the shock

+

+//since the flow is isentropic downstream of the shock, total pressure is conserved

+ps_atm = p0_2/101300;                       //pressure at the stagnation point

+

+printf("\nRESULTS\n---------\nThe pressure at the nose is:\n        p_s = %2.1f atm\n",ps_atm)
\ No newline at end of file
diff --git a/494/CH8/EX8.14/8_14.sce b/494/CH8/EX8.14/8_14.sce
new file mode 100755
index 000000000..335e585d9
--- /dev/null
+++ b/494/CH8/EX8.14/8_14.sce
@@ -0,0 +1,19 @@
+//All the quantities are expressedin SI units

+

+p1 = 2527.3;                    //ambient pressure at the altitude of 25 km

+T1 = 216.66;                    //ambient temperature at the altitude of 25 km

+p0_1 = 38800;                   //total pressure

+gam = 1.4;                      //ratio of specific heats

+R = 287;                        //universal gas constant

+pressure_ratio = p0_1/p1;       //ratio of total to static pressure

+

+//for this value of pressure ratio, mach number is

+M1 = 3.4;

+

+//the speed of sound is given by

+a1 = sqrt(gam*R*T1)

+

+//thus the velocity can be calculated as

+V1 = M1*a1;

+

+printf("\nRESULTS\n---------\nThe Velocity of the airplane is:\n        V1 = %4.0f m/s\n",V1)
\ No newline at end of file
diff --git a/494/CH8/EX8.2/8_2.sce b/494/CH8/EX8.2/8_2.sce
new file mode 100755
index 000000000..172a95fd3
--- /dev/null
+++ b/494/CH8/EX8.2/8_2.sce
@@ -0,0 +1,14 @@
+//All the quantities are expressed in SI units

+

+T = 320;            //static temperature

+V = 1000;           //velocity

+gam = 1.4;          //ratio of specific heats

+R = 287;            //universal gas constant

+

+//the speed of sound is given by

+a = sqrt(gam*R*T);

+

+//the mach number can be calculated as

+M = V/a;

+

+printf("\nRESULTS\n---------\nThe Mach number is:\n        M = %1.2f\n",M)
\ No newline at end of file
diff --git a/494/CH8/EX8.3/8_3.sce b/494/CH8/EX8.3/8_3.sce
new file mode 100755
index 000000000..e914df910
--- /dev/null
+++ b/494/CH8/EX8.3/8_3.sce
@@ -0,0 +1,19 @@
+//All the quantities are expressed in SI units

+

+gam = 1.4;                    //ratio of specific heats

+

+//(a)

+M = 2;                        //Mach number

+

+//the ratio of kinetic energy to internal energy is given by

+ratio = gam*(gam-1)*M*M/2;

+

+printf("\n(a)\nThe ratio of kinetic energy to internal energy is:\n\n                        %1.2f\n",ratio)

+

+//similarly for (b)

+//(b)

+M = 20;

+

+ratio = gam*(gam-1)*M*M/2;

+

+printf("\n(b)\nThe ratio of kinetic energy to internal energy is:\n\n                        %3.0f\n",ratio)
\ No newline at end of file
diff --git a/494/CH8/EX8.4/8_4.sce b/494/CH8/EX8.4/8_4.sce
new file mode 100755
index 000000000..b3ff15b2b
--- /dev/null
+++ b/494/CH8/EX8.4/8_4.sce
@@ -0,0 +1,14 @@
+//All the quantities are expressed in SI units

+

+M = 2.79;        //Mach number

+T = 320;         //static temperature from ex. 7.3

+p = 1;           //static pressure in atm

+gam = 1.4;

+

+//from eq. (8.40)

+T0 = T*(1+((gam-1)/2*M*M));

+

+//from eq. (8.42)

+p0 = p*((1+((gam-1)/2*M*M))^(gam/(gam-1)));

+

+printf("\nRESULTS\n---------\nThe total temperature and pressure are:\n        T0 = %3.0f K\n        P0 = %2.1f atm\n",T0,p0)
\ No newline at end of file
diff --git a/494/CH8/EX8.5/8_5.sce b/494/CH8/EX8.5/8_5.sce
new file mode 100755
index 000000000..7013ea9f1
--- /dev/null
+++ b/494/CH8/EX8.5/8_5.sce
@@ -0,0 +1,23 @@
+//All the quantities are expressed in SI units

+

+M = 3.5;        //Mach number

+T = 180;         //static temperature from ex. 7.3

+p = 0.3;           //static pressure in atm

+gam = 1.4;

+R = 287;

+

+//from eq. (8.40)

+T0 = T*(1+((gam-1)/2*M*M));

+

+//from eq. (8.42)

+p0 = p*((1+((gam-1)/2*M*M))^(gam/(gam-1)));

+

+a = sqrt(gam*R*T);

+V = a*M;

+

+//the values at local sonic point are given by

+T_star = T0*2/(gam+1);

+a_star = sqrt(gam*R*T_star);

+M_star = V/a_star;

+

+printf("\nRESULTS\n---------\n        T0 = %3.0f K\n        P0 = %2.1f atm\n        T* = %3.1f k\n        a* = %3.0f m/s\n        M* = %1.2f",T0,p0,T_star,a_star,M_star)
\ No newline at end of file
diff --git a/494/CH8/EX8.6/8_6.sce b/494/CH8/EX8.6/8_6.sce
new file mode 100755
index 000000000..48a5b2593
--- /dev/null
+++ b/494/CH8/EX8.6/8_6.sce
@@ -0,0 +1,19 @@
+//All the quantities are expressed in SI units

+

+p_inf = 1;

+p1 = 0.7545;

+M_inf = 0.6;

+gam = 1.4;

+

+//from eq. (8.42)

+p0_inf = p_inf*((1+((gam-1)/2*M_inf*M_inf))^(gam/(gam-1)));

+

+p0_1 = p0_inf;

+

+//from eq. (8.42)

+ratio = p0_1/p1;

+

+//from appendix A, for this ratio, the Mach number is

+M1 = 0.9;

+

+printf("\nRESULTS\n---------\nThe mach number at the given point is:\n        M1 = %1.1f\n",M1)
\ No newline at end of file
diff --git a/494/CH8/EX8.7/8_7.sce b/494/CH8/EX8.7/8_7.sce
new file mode 100755
index 000000000..43ffa89fa
--- /dev/null
+++ b/494/CH8/EX8.7/8_7.sce
@@ -0,0 +1,18 @@
+//All the quantities are expressed in SI units

+

+T_inf = 288;                                        //freestream temperature

+p_inf = 1;                                          //freestream pressure

+p1 = 0.7545;                                        //pressure at point 1

+M = 0.9;                                            //mach number at point 1

+gam = 1.4;                                          //ratio of specific heats

+

+//for isentropic flow, from eq. (7.32)

+T1 = T_inf*((p1/p_inf)^((gam-1)/gam));

+

+//the speed of sound at that point is thus

+a1 = sqrt(gam*R*T1);

+

+//thus, the velocity can be given as

+V1 = M*a1;

+

+printf("\nRESULTS\n---------\nThe velocity at the given point is:\n        V1 = %3.0f m/s\n",V1)
\ No newline at end of file
diff --git a/494/CH8/EX8.8/8_8.sce b/494/CH8/EX8.8/8_8.sce
new file mode 100755
index 000000000..8de9622cd
--- /dev/null
+++ b/494/CH8/EX8.8/8_8.sce
@@ -0,0 +1,26 @@
+//All the quantities are expressed in SI units

+

+u1 = 680;                            //velocity upstream of shock

+T1 = 288;                            //temperature upstream of shock

+p1 = 1;                              //pressure upstream of shock

+gam = 1.4;                           //ratio of specific heats

+R = 287;                             //universal gas constant

+

+//the speed of sound is given by

+a1 = sqrt(gam*R*T1)

+

+//thus the mach number is

+M1 = 2;

+

+//from Appendix B, for M = 2, the relations between pressure and temperature are given by

+pressure_ratio = 4.5;                //ratio of pressure accross shock

+temperature_ratio = 1.687;           //ratio of temperature accross shock

+M2 = 0.5774;                         //mach number downstream of shock

+

+//thus the values downstream of the shock can be calculated as

+p2 = pressure_ratio*p1;

+T2 = temperature_ratio*T1;

+a2 = sqrt(gam*R*T2);

+u2 = M2*a2;

+

+printf("\nRESULTS\n---------\n        p2 = %1.1f atm\n        T2 = %3.0f K\n        u2 = %3.0f m/s",p2,T2,u2)
\ No newline at end of file
diff --git a/494/CH8/EX8.9/8_9.sce b/494/CH8/EX8.9/8_9.sce
new file mode 100755
index 000000000..ada86a410
--- /dev/null
+++ b/494/CH8/EX8.9/8_9.sce
@@ -0,0 +1,27 @@
+//All the quantities are expressed in SI units

+

+p1 = 1;                                            //ambient pressure upstream of shock

+

+

+//(a)

+//for M = 2;

+p0_1 = 7.824*p1;                                   //total pressure upstream of shock

+pressure_ratio = 0.7209;                           //ratio of total pressure accross the shock

+p0_2 = pressure_ratio*p0_1;                        //total pressure downstream of shock

+

+//thus the total loss of pressure is given by

+pressure_loss = p0_1 - p0_2;

+

+printf("\nRESULTS\n---------\nThe total pressure loss is:\n(a)        P0_loss = %1.3f atm\n",pressure_loss)

+

+//similarly

+//(b)

+//for M = 4;

+p0_1 = 151.8*p1;

+pressure_ratio = 0.1388;

+p0_2 = pressure_ratio*p0_1;

+

+//thus the total loss of pressure is given by

+pressure_loss = p0_1 - p0_2;

+

+printf("\n(b)        P0_loss = %3.1f atm\n",pressure_loss)
\ No newline at end of file