6 files changed, 100 insertions, 0 deletions
diff --git a/1460/CH13/EX13.1/13_1.sce b/1460/CH13/EX13.1/13_1.sce
new file mode 100755
index 000000000..74c25e615
--- /dev/null
+++ b/1460/CH13/EX13.1/13_1.sce
@@ -0,0 +1,17 @@
+clc
+//initialization of variables
+v=2000 //ft/sec
+P=14.7 //lb/in^2
+g=1.4
+T=10+460 //R
+//calculations
+c=sqrt(g*32.2*53.3*T)
+Nm=v/c
+Tratio=1+ (g-1)/2 *Nm^2
+Tt=Tratio*T
+Pratio=(Tratio)^(g/(g-1))
+Pt=Pratio*P
+//results
+printf("Stagnation temperature = %d R",Tt)
+printf("\n Stagnation pressure = %.1f lb/in^2",Pt)
+//The answers are a bit different due to rounding off error.
diff --git a/1460/CH13/EX13.2/13_2.sce b/1460/CH13/EX13.2/13_2.sce
new file mode 100755
index 000000000..486877262
--- /dev/null
+++ b/1460/CH13/EX13.2/13_2.sce
@@ -0,0 +1,11 @@
+clc
+//initialization of variables
+A=0.3 //ft^2
+P=30 //lb/in^2
+T=160+460 //R
+Mn=0.82
+g=1.4
+//calculations
+w=A*144*P*sqrt(g*32.2) *Mn*(1+ (g-1)/2 *(Mn)^2)^(-3) /sqrt(53.3*T)
+//results
+printf("Mass flow = %.1f lbm/sec",w)
diff --git a/1460/CH13/EX13.3/13_3.sce b/1460/CH13/EX13.3/13_3.sce
new file mode 100755
index 000000000..df59b0cd5
--- /dev/null
+++ b/1460/CH13/EX13.3/13_3.sce
@@ -0,0 +1,21 @@
+clc
+//initialization of variables
+Mn=3
+Mni=0.2
+w=10 //lbm/sec
+g=1.4
+P=200 //lb/in^2
+T=400+460 //R
+//calculations
+Astar=w*sqrt(53.3*T) *((g+1)/2)^3 /(P*sqrt(g*32.2))
+A1ratio=(2/(g+1) + (g-1)*Mni^2 /(g+1))^3 /Mni
+A1=A1ratio*Astar
+A2ratio=(2/(g+1) + (g-1)*Mn^2 /(g+1))^3 /Mn
+A2=A2ratio*Astar
+Pexit=P/(1+ Mni*Mn^2)^(g/(g-1))
+//results
+printf("Throat Area = %.2f in^2",Astar)
+printf("\n Inlet Area = %.2f in^2",A1)
+printf("\n Exit Area = %.2f in^2",A2)
+printf("\n Exit pressure = %.2f lb/in^2",Pexit)
+//There is a printing mistake in the textbook for the formula of Exit area
diff --git a/1460/CH13/EX13.4/13_4.sce b/1460/CH13/EX13.4/13_4.sce
new file mode 100755
index 000000000..d43ce08be
--- /dev/null
+++ b/1460/CH13/EX13.4/13_4.sce
@@ -0,0 +1,18 @@
+clc
+//initialization of variables
+Pi=750 //lb/in^2
+g=1.25
+TA=2 //in^2
+r=3
+//calculations
+Fstar=(g+1)*(2/(g+1))^5 *TA*750
+Me=2.45
+Fratio=(1+g*Me^2)/(Me*(sqrt(4.5+ (g^2 -1)*Me^2)))
+F2=Fratio*Fstar
+Pratio=(1+ 0.2*Me^2)^5
+Fnstar=Fratio-((g+1)/2)^5 *r/(Pratio*2.25)
+Fn=Fnstar*Fstar
+//results
+printf("Internal rocket thrust = %d lb",F2)
+printf("\n External thrust = %d lb",Fn)
+//The calculation for Fstar in textbook is wrong
diff --git a/1460/CH13/EX13.5/13_5.sce b/1460/CH13/EX13.5/13_5.sce
new file mode 100755
index 000000000..f05efa61a
--- /dev/null
+++ b/1460/CH13/EX13.5/13_5.sce
@@ -0,0 +1,17 @@
+clc
+//initialization of variables
+Tt2=1620+460 //R
+Tt1=60+460 //R
+Mi=0.2
+P=40 //lb/in^2
+g=1.35
+//calculations
+Tratio=Tt2/Tt1
+disp("From figure")
+fM=4*0.036
+NM2=0.49
+Pratio=0.98/0.885
+Pt2=P/Pratio
+//results
+printf("Final stagnation pressure = %.1f //lb/in^2",Pt2)
+printf("\n Final mach number = %.3f",fM)
diff --git a/1460/CH13/EX13.6/13_6.sce b/1460/CH13/EX13.6/13_6.sce
new file mode 100755
index 000000000..21082dc5c
--- /dev/null
+++ b/1460/CH13/EX13.6/13_6.sce
@@ -0,0 +1,16 @@
+clc
+//initialization of variables
+M=0.4
+l=10 //ft
+dia= 3 //in
+P=50 //lb/in^2
+ff=0.008
+T=100+460 //R
+//calculations
+constant= 4*ff*l/dia
+exitM=2.9-constant
+Nm2=0.5
+Ptratio=2.73/2.3
+Pt2=P/Ptratio
+//results
+printf("Exit total pressure = %.1f lb/in^2",Pt2)