24 files changed, 227 insertions, 0 deletions

diff --git a/629/CH12/EX12.1/ex12_1.txt b/629/CH12/EX12.1/ex12_1.txt
new file mode 100644
index 000000000..50cf5ff23
--- /dev/null
+++ b/629/CH12/EX12.1/ex12_1.txt
@@ -0,0 +1,3 @@
+ 

+ The speed of sound in air at 15°C, c = 340 m/s.

+ 
\ No newline at end of file
diff --git a/629/CH12/EX12.1/example12_1.sce b/629/CH12/EX12.1/example12_1.sce
new file mode 100644
index 000000000..80ad3445a
--- /dev/null
+++ b/629/CH12/EX12.1/example12_1.sce
@@ -0,0 +1,9 @@
+clear

+clc

+//Example 12.1 SPEED OF SOUND CALCULATION

+R=287; //gas constant [J/Kg.K]

+k=1.4;

+T=15+273; //temperature [K]

+//Speed of sound

+c=sqrt(k*R*T) //[m/s]

+printf("\n The speed of sound in air at 15°C, c = %.f m/s.\n",c)
\ No newline at end of file
diff --git a/629/CH12/EX12.10/ex12_10.txt b/629/CH12/EX12.10/ex12_10.txt
new file mode 100644
index 000000000..b661e3a0f
--- /dev/null
+++ b/629/CH12/EX12.10/ex12_10.txt
@@ -0,0 +1,2 @@
+ 

+ Because (pe=38.7) < (pb=100), the nozzle is overexpanded.
\ No newline at end of file
diff --git a/629/CH12/EX12.10/example12_10.sce b/629/CH12/EX12.10/example12_10.sce
new file mode 100644
index 000000000..77d9d7ce2
--- /dev/null
+++ b/629/CH12/EX12.10/example12_10.sce
@@ -0,0 +1,10 @@
+clear

+clc

+//Example 12.10 NOZZLE EXIT CONDITION

+k=1.4;

+//From table A.1, interpolating for A/Ao=4,

+M=2.94; //Mach number

+pb=100; //back pressure[kPa]

+pt=1300; //total pressure[kPa]

+pe=pt/((1+[(k-1)/2]*M^2)^(k/(k-1))) //[kPa]

+printf("\n Because (pe=%.1f) < (pb=%.f), the nozzle is overexpanded.\n",pe,pb)
\ No newline at end of file
diff --git a/629/CH12/EX12.11/ex12_11.txt b/629/CH12/EX12.11/ex12_11.txt
new file mode 100644
index 000000000..8530424f3
--- /dev/null
+++ b/629/CH12/EX12.11/ex12_11.txt
@@ -0,0 +1,3 @@
+ 

+ The static pressure at the exit = 603 kPa.

+ 
\ No newline at end of file
diff --git a/629/CH12/EX12.11/example12_11.sce b/629/CH12/EX12.11/example12_11.sce
new file mode 100644
index 000000000..7fff6f466
--- /dev/null
+++ b/629/CH12/EX12.11/example12_11.sce
@@ -0,0 +1,24 @@
+clear

+clc

+//Example 12.11 SHOCK WAVE IN LAVAL NOZZLE

+k=1.4;

+AoA=1/2 ;//AoA=(Ao/A)

+AeAo=4; //AeAo=(Ae/Ao)

+//From table A.1, interpolation for A/Ao=2,

+//for supersonic flow

+M1=2.2;

+//for normal shock

+M2=0.547;

+pt21=0.6281; //pt21=(pt2/pt1)

+pt1=1000; //[kPa]

+pt2=pt21*pt1 //[kPa]

+//for subsonic part at M=M2,

+AAv=1.26; //AAv=(A/Av)

+//Exit area ratio

+//Ae/Av=(Ae/Ao)*(Ao/A)*(A/Av)

+AeAv=AeAo*AoA*AAv //AeAv=(Ae/Av)

+//for subsonic flow at A/Ao=(Ae/Av)

+M=0.24; 

+//Exit pressure

+pe=pt2/((1+(k-1)*M^2/2)^(k/(k-1))) //[kPa]

+printf("\n The static pressure at the exit = %.f kPa.\n",pe)
\ No newline at end of file
diff --git a/629/CH12/EX12.12/ex12_12.txt b/629/CH12/EX12.12/ex12_12.txt
new file mode 100644
index 000000000..ad41c1119
--- /dev/null
+++ b/629/CH12/EX12.12/ex12_12.txt
@@ -0,0 +1,2 @@
+ 

+ The mass flow rate = 0.238 kg/s.
\ No newline at end of file
diff --git a/629/CH12/EX12.12/example12_12.sce b/629/CH12/EX12.12/example12_12.sce
new file mode 100644
index 000000000..df847404a
--- /dev/null
+++ b/629/CH12/EX12.12/example12_12.sce
@@ -0,0 +1,20 @@
+clear

+clc

+//Example 12.12 MASS FLOW IN TRUNCATED NOZZLE

+k=1.4;

+d=0.03; //diameter[m]

+A=%pi*d^2/4 //area[m^2]

+pt=160; //[kPa]

+pb=100; //[kPa]

+Tt=273+80; //total temp.[K]

+//Mach number at exit

+Me=sqrt((2/(k-1))*[(pt/pb)^((k-1)/k)-1])

+//Static temperature at exit

+Te=Tt/(1+((k-1)/2)*Me^2) //[K]

+R=287; //[J/kg.K]

+//Static density at exit

+rho=pb*10^3/(R*Te) //[kg/m^3]

+c=sqrt(k*R*Te) //speed of sound[m/s]

+//Mass flow rate

+m=rho*A*Me*c //[kg/s]

+printf("\n The mass flow rate = %.3f kg/s.\n",m)
\ No newline at end of file
diff --git a/629/CH12/EX12.2/ex12_2.txt b/629/CH12/EX12.2/ex12_2.txt
new file mode 100644
index 000000000..dc9b178d2
--- /dev/null
+++ b/629/CH12/EX12.2/ex12_2.txt
@@ -0,0 +1,3 @@
+ 

+ The Mach number of the aircraft, M = 1.58.

+ 
\ No newline at end of file
diff --git a/629/CH12/EX12.2/example12_2.sce b/629/CH12/EX12.2/example12_2.sce
new file mode 100644
index 000000000..d693c926e
--- /dev/null
+++ b/629/CH12/EX12.2/example12_2.sce
@@ -0,0 +1,16 @@
+clear

+clc

+//Example 12.2 MACH-NUMBER CALCULATION

+z=13; //[km]

+alpha=5.87; //[K/km]

+To=296; //[K]

+//Temperature at z

+T=To-alpha*z //[K]

+R=287; //[J/Kg.K]

+k=1.4;

+//Speed of sound

+c=sqrt(k*R*T) //[m/s]

+V=470; //speed of fighter[m/s]

+//Mach number

+M=V/c

+printf("\n The Mach number of the aircraft, M = %.2f.\n",M)
\ No newline at end of file
diff --git a/629/CH12/EX12.3/ex12_3.txt b/629/CH12/EX12.3/ex12_3.txt
new file mode 100644
index 000000000..b9f026826
--- /dev/null
+++ b/629/CH12/EX12.3/ex12_3.txt
@@ -0,0 +1,2 @@
+ 

+ The surface temperature of the aircraft = 337 K.
\ No newline at end of file
diff --git a/629/CH12/EX12.3/example12_3.sce b/629/CH12/EX12.3/example12_3.sce
new file mode 100644
index 000000000..d9e9cb90b
--- /dev/null
+++ b/629/CH12/EX12.3/example12_3.sce
@@ -0,0 +1,9 @@
+clear

+clc

+//Example 12.3 TOTAL TEMPERATURE CALCULATION

+T=273+(-50) //static temperature [K]

+k=1.4;

+M=1.6; //Mach number

+//Total temperature

+Tt=T*(1+(k-1)*M^2/2) //[K]

+printf("\n The surface temperature of the aircraft = %.f K.\n",Tt)
\ No newline at end of file
diff --git a/629/CH12/EX12.4/ex12_4.txt b/629/CH12/EX12.4/ex12_4.txt
new file mode 100644
index 000000000..7c7ae6ac9
--- /dev/null
+++ b/629/CH12/EX12.4/ex12_4.txt
@@ -0,0 +1,2 @@
+ 

+ The drag force on the sphere = 2.58 N.
\ No newline at end of file
diff --git a/629/CH12/EX12.4/example12_4.sce b/629/CH12/EX12.4/example12_4.sce
new file mode 100644
index 000000000..3cf8712ef
--- /dev/null
+++ b/629/CH12/EX12.4/example12_4.sce
@@ -0,0 +1,13 @@
+clear

+clc

+//Example 12.4 DRAG FORCE ON A SPHERE

+k=1.4;

+p=101; //pressure[kPa]

+M=0.7; //Mach number

+q=k*p*M^2/2 //kinetic pressure[kPa]

+CD=0.95;

+D=0.01; //[m]

+A=%pi*D^2/4 //area[m^2]

+//Drag force

+FD=CD*q*A*10^3 //[N]

+printf("\n The drag force on the sphere = %.2f N.\n",FD)
\ No newline at end of file
diff --git a/629/CH12/EX12.5/ex12_5.txt b/629/CH12/EX12.5/ex12_5.txt
new file mode 100644
index 000000000..fd0cafe91
--- /dev/null
+++ b/629/CH12/EX12.5/ex12_5.txt
@@ -0,0 +1,9 @@
+ 

+The Mach number for downstream of the shock wave, M = 0.668.

+

+

+The pressure for downstream of the shock wave, P = 282 kPa, absolute.

+

+

+The temperature for downstream of the shock wave, T = 400 K or 127°C.

+ 
\ No newline at end of file
diff --git a/629/CH12/EX12.5/example12_5.sce b/629/CH12/EX12.5/example12_5.sce
new file mode 100644
index 000000000..1848c77e1
--- /dev/null
+++ b/629/CH12/EX12.5/example12_5.sce
@@ -0,0 +1,16 @@
+clear

+clc

+//Example 12.5 PROPERTY CHANGES ACROSS NORMAL SHOCK WAVE

+k=1.4;

+M1=1.6; //Upstream Mach number

+p1=100; //pressure[kPa]

+T1=15+273; //[K]

+//Downstream Mach number

+M2=sqrt(((k-1)*M1^2+2)/(2*k*M1^2-(k-1)))

+printf("\nThe Mach number for downstream of the shock wave, M = %.3f.\n\n",M2)

+//Downstream pressure

+p2=p1*[(1+k*M1^2)/(1+k*M2^2)] //[kPa]

+printf("\nThe pressure for downstream of the shock wave, P = %.f kPa, absolute.\n\n",p2)

+//Downstream temperature

+T2=T1*{(1+[(k-1)/2]*M1^2)/(1+[(k-1)/2]*M2^2)} //[K]

+printf("\nThe temperature for downstream of the shock wave, T = %.f K or %.f°C.\n",T2,T2-273)
\ No newline at end of file
diff --git a/629/CH12/EX12.6/ex12_6.txt b/629/CH12/EX12.6/ex12_6.txt
new file mode 100644
index 000000000..51179500f
--- /dev/null
+++ b/629/CH12/EX12.6/ex12_6.txt
@@ -0,0 +1,3 @@
+

+ The change in entropy across the wave = 20.5 J/kg.K.

+ 
\ No newline at end of file
diff --git a/629/CH12/EX12.6/example12_6.sce b/629/CH12/EX12.6/example12_6.sce
new file mode 100644
index 000000000..f50a6ce45
--- /dev/null
+++ b/629/CH12/EX12.6/example12_6.sce
@@ -0,0 +1,20 @@
+clear

+clc

+//Example 12.6 ENTROPY INCREASE ACROSS SHOCK WAVE

+//To find Approx Value

+function [A]= approx (V,n)

+    A= round(V*10^n)/10^n; //V-Value, n-to what place

+    funcprot (0)

+endfunction

+k=1.4;

+M1=1.5;

+//Downstream Mach number

+M2=approx(sqrt(((k-1)*M1^2+2)/(2*k*M1^2-(k-1))),3)

+//Pressure ratio, (p21=p2/p1)

+p21=approx([(1+k*M1^2)/(1+k*M2^2)],2)

+//Temperature ratio, (T21=T2/T1)

+T21=approx((1+[(k-1)/2]*M1^2)/(1+[(k-1)/2]*M2^2),2)

+R=287; //[J/kg.K]

+//Entropy change

+del_s=R*log((T21^(k/(k-1))/p21)) //[J/kg.K]

+printf("\n The change in entropy across the wave = %.1f J/kg.K.\n",del_s)
\ No newline at end of file
diff --git a/629/CH12/EX12.7/ex12_7.txt b/629/CH12/EX12.7/ex12_7.txt
new file mode 100644
index 000000000..2721bfa5a
--- /dev/null
+++ b/629/CH12/EX12.7/ex12_7.txt
@@ -0,0 +1,2 @@
+ 

+ The cross-sectional area of the test section, A = 42.3 cm^2.
\ No newline at end of file
diff --git a/629/CH12/EX12.7/example12_7.sce b/629/CH12/EX12.7/example12_7.sce
new file mode 100644
index 000000000..7c0f8a7b0
--- /dev/null
+++ b/629/CH12/EX12.7/example12_7.sce
@@ -0,0 +1,9 @@
+clear

+clc

+//Example 12.7 TEST SECTION SIZE IN SUPERSONIC WIND TUNNEL

+k=1.4;

+M=3; //Mach number

+Ao=10; //area[cm^2]

+//Cross-sectional area

+A=Ao*(1/M)*{(1+[(k-1)/2]*M^2)/((k+1)/2)}^((k+1)/(2*(k-1))) //[cm^2]

+printf("\n The cross-sectional area of the test section, A = %.1f cm^2.\n",A)
\ No newline at end of file
diff --git a/629/CH12/EX12.8/ex12_8.txt b/629/CH12/EX12.8/ex12_8.txt
new file mode 100644
index 000000000..d2264ac13
--- /dev/null
+++ b/629/CH12/EX12.8/ex12_8.txt
@@ -0,0 +1,9 @@
+ 

+ The Mach number at the test section, M = 3.91.

+

+

+ At the test section, pressure p = 29.7 kPa and temperature T = 86 K.

+

+

+ The velocity at test section, V = 727 m/s.

+ 
\ No newline at end of file
diff --git a/629/CH12/EX12.8/example12_8.sce b/629/CH12/EX12.8/example12_8.sce
new file mode 100644
index 000000000..fa95625a4
--- /dev/null
+++ b/629/CH12/EX12.8/example12_8.sce
@@ -0,0 +1,19 @@
+clear

+clc

+//Example 12.8 FLOW PROPERTIES IN SUPERSONIC WIND TUNNEL

+k=1.4;

+R=287; //[J/kg.K]

+//From table A.1, interpolating for A/Ao=10,

+M=3.91; //Mach number

+printf("\n The Mach number at the test section, M = %.2f.\n\n",M)

+pt=4000; //pressure[kPa]

+Tt=350; //temp.[K]

+//In test section

+p=0.00743*pt //[kPa]

+T=0.246*Tt //[K]

+printf("\n At the test section, pressure p = %.1f kPa and temperature T = %.f K.\n\n",p,T)

+//Speed of sound

+c=sqrt(k*R*T) //[m/s]

+//Velocity

+V=M*c //[m/s]

+printf("\n The velocity at test section, V = %.f m/s.\n",V)
\ No newline at end of file
diff --git a/629/CH12/EX12.9/ex12_9.txt b/629/CH12/EX12.9/ex12_9.txt
new file mode 100644
index 000000000..6259f24c3
--- /dev/null
+++ b/629/CH12/EX12.9/ex12_9.txt
@@ -0,0 +1,3 @@
+ 

+ The mass flow rate = 14.8 kg/s.

+ 
\ No newline at end of file
diff --git a/629/CH12/EX12.9/example12_9.sce b/629/CH12/EX12.9/example12_9.sce
new file mode 100644
index 000000000..c7d9e299b
--- /dev/null
+++ b/629/CH12/EX12.9/example12_9.sce
@@ -0,0 +1,19 @@
+clear

+clc

+//Example 12.9 MASS FLOW RATE IN SUPERSONIC WIND TUNNEL

+k=1.4;

+R=287; //[J/kg.K]

+M=3; //Mach number

+A=225*10^-4; //[m^2]

+//Throat area

+Ao=A/((1/M)*{(1+[(k-1)/2]*M^2)/((k+1)/2)}^((k+1)/(2*(k-1)))) //[m^2]

+//Static T,p 

+T=273+(-20) //[K]

+p=50; //[kPa]

+//Total temperature

+Tt=T*(1+(k-1)*M^2/2) //[K]

+//Total pressure

+pt=p*(1+(k-1)*M^2/2)^(k/(k-1)) //[kPa]

+//Mass flow rate

+m=k^(1/2)*[(2/(k+1))^((k+1)/(2*(k-1)))]*pt*10^3*Ao/((R*Tt)^(1/2)) //[kg]

+printf("\n The mass flow rate = %.1f kg/s.\n",m)
\ No newline at end of file