diff options
Diffstat (limited to '3685/CH17')
| -rw-r--r-- | 3685/CH17/EX17.1/Ex17_1.sce | 53 | ||||
| -rw-r--r-- | 3685/CH17/EX17.1/Ex17_1.txt | 8 | ||||
| -rw-r--r-- | 3685/CH17/EX17.2/Ex17_2.sce | 42 | ||||
| -rw-r--r-- | 3685/CH17/EX17.2/Ex17_2.txt | 8 | ||||
| -rw-r--r-- | 3685/CH17/EX17.3/Ex17_3.sce | 44 | ||||
| -rw-r--r-- | 3685/CH17/EX17.3/Ex17_3.txt | 14 | ||||
| -rw-r--r-- | 3685/CH17/EX17.4/Ex17_4.sce | 22 | ||||
| -rw-r--r-- | 3685/CH17/EX17.4/Ex17_4.txt | 4 | ||||
| -rw-r--r-- | 3685/CH17/EX17.5/Ex17_5.sce | 34 | ||||
| -rw-r--r-- | 3685/CH17/EX17.5/Ex17_5.txt | 7 |
10 files changed, 236 insertions, 0 deletions
diff --git a/3685/CH17/EX17.1/Ex17_1.sce b/3685/CH17/EX17.1/Ex17_1.sce new file mode 100644 index 000000000..8b7f4636d --- /dev/null +++ b/3685/CH17/EX17.1/Ex17_1.sce @@ -0,0 +1,53 @@ +clc
+t0 = 37 // Stangnation temperature in degree Celsius
+P = 40 // Duct static pressure in kPa
+g = 1.4 // Heat capacity ratio
+function [x] = speed(a,b,f)
+ N = 100
+ eps = 1e-5;
+ if((f(a)*f(b))>0) then
+ error('no root possible f(a)*f(b)>0');
+ abort;
+ end;
+ if(abs(f(a))<eps) then
+ error('solution at a');
+ abort;
+ end
+ if(abs(f(b))<eps) then
+ error('solution at b');
+ abort;
+ end
+ while(N>0)
+ c = (a+b)/2
+ if(abs(f(c))<eps) then
+ x = c ;
+ x;
+ return;
+ end;
+ if((f(a)*f(c))<0 ) then
+ b = c ;
+ else
+ a = c ;
+ end
+ N = N-1;
+ end
+ error('no convergence');
+ abort;
+endfunction
+
+deff('[y]=p(x)',['y = x^4 + (5*(x^2)) - 3.225 '])
+x = speed(0.5,1,p);
+T0 = t0+273;
+M = x; // Mach number
+g = 1.4; // gamma
+R = 0.287;
+T = T0/(1+((g-1)/2)*M^2);
+c = sqrt(g*R*T*1000);
+V = c*M;
+P0 = P*((T0/T)^(g/(g-1)));
+
+printf("\n Example 17.1\n")
+printf("\n Mach number is %f ",M)
+printf("\n Velocity is %f m/s",V)
+printf("\n Stagnation pressure is %f kPa",P0)
+//The answers vary due to round off error
diff --git a/3685/CH17/EX17.1/Ex17_1.txt b/3685/CH17/EX17.1/Ex17_1.txt new file mode 100644 index 000000000..17e15f0fd --- /dev/null +++ b/3685/CH17/EX17.1/Ex17_1.txt @@ -0,0 +1,8 @@ +
+ Example 17.2
+
+ Mass flow rate of air through diffuser is 59.420029 Kg/s
+ Mach number of leaving air is 0.135000
+ Temperature of leaving air is 71.429075 degree celcius
+ Pressure of leaving air is 0.260472 MPa
+ Net thrust is 51.328446 kN
\ No newline at end of file diff --git a/3685/CH17/EX17.2/Ex17_2.sce b/3685/CH17/EX17.2/Ex17_2.sce new file mode 100644 index 000000000..ae38b97bb --- /dev/null +++ b/3685/CH17/EX17.2/Ex17_2.sce @@ -0,0 +1,42 @@ +clc
+P1 = 0.18 // Diffuser static pressure in MPa
+R = 0.287 // Gas constant
+T1 = 37 // Static temperature
+P0 = 0.1// Atmospheric pressure in MPa
+A1 = 0.11 // intake area in m^2
+V1 = 267 // Inlet velocity in m/s
+w = (P1*1e3/(R*(T1+273)))*A1*V1 // mass flow rate
+g = 1.4 // Heat capacity ratio
+c1 = sqrt(g*R*(T1+273)*1000) // velocity
+M1 = V1/c1 // Mach number
+A1A_ = 1.0570 // A1/A* A* = A_
+P1P01 = 0.68207 // pressure ratio
+T1T01 = 0.89644// Temperature ratio
+F1F_ = 1.0284// Impulse function ratio
+A2A1 = 0.44/0.11 // Area ratio
+A2A_ = A2A1*A1A_// Area ratio
+M2 = 0.135 // Mach number
+P2P02 = 0.987 // Pressure ratio
+T2T02 = 0.996 // Temperature ratio
+F2F_ = 3.46// Impulse function ratio
+P2P1 = P2P02/P1P01 // Pressure ratio
+T2T1 = T2T02/T1T01// Temperature ratio
+F2F1 = F2F_/F1F_ // Impulse function ratio
+P2 = P2P1*P1 // Outlet pressure
+T2 = T2T1*(T1+273) // Outlet temperature
+A2 = A2A1*A1 // Exit area
+F1 = P1*A1*(1+g*M1^2) // Impulse function
+F2 = F2F1*F1 // Impulse function
+Tint = F2-F1 // Internal thrust
+Text = P0*(A2-A1) // External thrust
+NT = Tint - Text // Net thrust
+
+printf("\n Example 17.2 \n")
+printf("\n Mass flow rate of air through diffuser is %f Kg/s",w)
+printf("\n Mach number of leaving air is %f ",M2)
+printf("\n Temperature of leaving air is %f degree celcius",T2-273)
+printf("\n Pressure of leaving air is %f MPa ",P2)
+printf("\n Net thrust is %f kN",NT*1e3)
+
+//The answers vary due to round off error
+
diff --git a/3685/CH17/EX17.2/Ex17_2.txt b/3685/CH17/EX17.2/Ex17_2.txt new file mode 100644 index 000000000..17e15f0fd --- /dev/null +++ b/3685/CH17/EX17.2/Ex17_2.txt @@ -0,0 +1,8 @@ +
+ Example 17.2
+
+ Mass flow rate of air through diffuser is 59.420029 Kg/s
+ Mach number of leaving air is 0.135000
+ Temperature of leaving air is 71.429075 degree celcius
+ Pressure of leaving air is 0.260472 MPa
+ Net thrust is 51.328446 kN
\ No newline at end of file diff --git a/3685/CH17/EX17.3/Ex17_3.sce b/3685/CH17/EX17.3/Ex17_3.sce new file mode 100644 index 000000000..97f9045ab --- /dev/null +++ b/3685/CH17/EX17.3/Ex17_3.sce @@ -0,0 +1,44 @@ +clc
+M2 = 2.197 // Mach number
+P2P0 = 0.0939 // pressure ratio
+T2T0 = 0.5089 // Temperature ratio
+P0 = 1 // Stagnation pressure in MPa
+T0 = 360 // Stagnation temperature in K
+g = 1.4 // Heat capacity ratio
+R = 0.287 // Gas constant
+P2 = P2P0*P0*1e3 // Static Pressure
+T2 = T2T0*T0 // Static temperature
+c2 = sqrt(g*R*T2*1000)
+V2 = c2*M2 //velocity at the exit from the nozzle
+// for air
+P_P0 = 0.528 // pressure ratio
+T_T0 = 0.833 // Temperature ratio
+P_ = P_P0*P0*1e3 // Static Pressure
+T_ = T_T0*T0 //Static temperature
+rho_ = P_/(R*T_) // density
+V_ = sqrt(g*R*T_*1000) // Velocity at the exit from the nozzle
+At = 500e-06 // throat area
+w = At*V_*rho_// Maximum flow rate of air
+
+printf("\n Example 17.3\n")
+printf("\n When divergent section act as a nozzle")
+printf("\n Maximum flow rate of air is %f kg/s",w)
+printf("\n Static temperature is %f K",T2)
+printf("\n Static Pressure is %f kPa",P2)
+printf("\n Velocity at the exit from the nozzle is %f m/s",V2)
+//The answers vary due to round off error
+
+// Part (b)
+Mb = 0.308 // Mach number
+P2P0b = 0.936 // Pressure ratio
+T2T0b = 0.9812 // Temperature ratio
+P2b = P2P0b*P0*1e3//Static Pressure
+T2b = T2T0b*T0 // Static temperature
+c2b = sqrt(g*R*T2b*1000) // Velocity
+V2b = c2b*Mb //Velocity at the exit from the nozzle
+printf("\n\n When divergent section act as a diffuser")
+printf("\n Maximum flow rate of air is %f kg/s",w)
+printf("\n Static temperature is %f K",T2b)
+printf("\n Static Pressure is %d kPa",P2b)
+printf("\n Velocity at the exit from the nozzle is %d m/s",V2b)
+
diff --git a/3685/CH17/EX17.3/Ex17_3.txt b/3685/CH17/EX17.3/Ex17_3.txt new file mode 100644 index 000000000..c06b09a63 --- /dev/null +++ b/3685/CH17/EX17.3/Ex17_3.txt @@ -0,0 +1,14 @@ +
+ Example 17.3
+
+ When divergent section act as a nozzle
+ Maximum flow rate of air is 1.064764 kg/s
+ Static temperature is 183.204000 K
+ Static Pressure is 93.900000 kPa
+ Velocity at the exit from the nozzle is 596.077184 m/s
+
+ When divergent section act as a diffuser
+ Maximum flow rate of air is 1.064764 kg/s
+ Static temperature is 353.232000 K
+ Static Pressure is 936 kPa
+ Velocity at the exit from the nozzle is 116 m/s
\ No newline at end of file diff --git a/3685/CH17/EX17.4/Ex17_4.sce b/3685/CH17/EX17.4/Ex17_4.sce new file mode 100644 index 000000000..0774f5333 --- /dev/null +++ b/3685/CH17/EX17.4/Ex17_4.sce @@ -0,0 +1,22 @@ +clc
+Px = 16 // pressure in kPa
+Poy = 70 //pressure in kPa
+Mx = 1.735 // Mach number
+Pyx = 3.34 // Pressure ratio
+rho_yx = 2.25 // Density ratio
+Tyx = 1.483 // Temperature ratio
+Poyox = 0.84 // pressure ratio
+My = 0.631 // Mach number
+g = 1.4 // Ratio of heat capacities
+Tox = 573 // stagnation temperature in K
+Toy = Tox // temperature equivalence
+Tx = Tox/(1+((g-1)/2)*Mx^2) // temperature at x
+Ty = Tyx*Tx // temperature at y
+Pox = Poy/Poyox // total pressure
+// From table
+Mx = 1.735
+
+printf("\n Example 17.4\n")
+printf("\n Mach number of the tunnel is %f ",Mx)
+
+
diff --git a/3685/CH17/EX17.4/Ex17_4.txt b/3685/CH17/EX17.4/Ex17_4.txt new file mode 100644 index 000000000..3a582d255 --- /dev/null +++ b/3685/CH17/EX17.4/Ex17_4.txt @@ -0,0 +1,4 @@ +
+ Example 17.4
+
+ Mach number of the tunnel is 1.735000
\ No newline at end of file diff --git a/3685/CH17/EX17.5/Ex17_5.sce b/3685/CH17/EX17.5/Ex17_5.sce new file mode 100644 index 000000000..159b22b22 --- /dev/null +++ b/3685/CH17/EX17.5/Ex17_5.sce @@ -0,0 +1,34 @@ +clc
+Ax = 18.75 // cross sectional area in divergent part in m^2
+A_ = 12.50 // throat area in m^2
+AA_ = 1.5 // Area ratio
+Pxox = 0.159 // pressure ratio from table
+R = 0.287 // Gas constant
+Pox = 0.21e03 // pressure in kPa
+Px = Pxox*Pox // pressure calculation
+// from the gas table on normal shock
+Mx = 1.86
+My = 0.604
+Pyx = 3.87
+Poyx = 4.95
+Poyox = 0.786
+Py = Pyx*Px
+Poy = Poyx*Px
+My = 0.604
+Ay_ = 1.183
+A2 = 25
+Ay = 18.75
+A2_ = (A2/Ay)*Ay_
+// From isentropic table
+M2 = 0.402
+P2oy = 0.895
+P2 = P2oy*Poy
+syx = -R*log(Poy/Pox) // sy-sx
+
+printf("\n Example 17.5\n")
+printf("\n Exit Mach number is %f ",M2)
+printf("\n Exit pressure is %f kPa",P2)
+printf("\n Exit Stagnation pressure is %f kPa",Pox-Poy)
+printf("\n Entropy increase is %f kJ/kg K",syx)
+//The answers vary due to round off error
+
diff --git a/3685/CH17/EX17.5/Ex17_5.txt b/3685/CH17/EX17.5/Ex17_5.txt new file mode 100644 index 000000000..7d8f1a7e9 --- /dev/null +++ b/3685/CH17/EX17.5/Ex17_5.txt @@ -0,0 +1,7 @@ +
+ Example 17.5
+
+ Exit Mach number is 0.402000
+ Exit pressure is 147.926048 kPa
+ Exit Stagnation pressure is 44.719500 kPa
+ Entropy increase is 0.068726 kJ/kg K
\ No newline at end of file |