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| author | prashantsinalkar | 2017-10-10 12:27:19 +0530 |
|---|---|---|
| committer | prashantsinalkar | 2017-10-10 12:27:19 +0530 |
| commit | 7f60ea012dd2524dae921a2a35adbf7ef21f2bb6 (patch) | |
| tree | dbb9e3ddb5fc829e7c5c7e6be99b2c4ba356132c /3685/CH21/EX21.8 | |
| parent | b1f5c3f8d6671b4331cef1dcebdf63b7a43a3a2b (diff) | |
| download | Scilab-TBC-Uploads-7f60ea012dd2524dae921a2a35adbf7ef21f2bb6.tar.gz Scilab-TBC-Uploads-7f60ea012dd2524dae921a2a35adbf7ef21f2bb6.tar.bz2 Scilab-TBC-Uploads-7f60ea012dd2524dae921a2a35adbf7ef21f2bb6.zip | |
initial commit / add all books
Diffstat (limited to '3685/CH21/EX21.8')
| -rw-r--r-- | 3685/CH21/EX21.8/Ex21_8.sce | 23 | ||||
| -rw-r--r-- | 3685/CH21/EX21.8/Ex21_8.txt | 5 |
2 files changed, 28 insertions, 0 deletions
diff --git a/3685/CH21/EX21.8/Ex21_8.sce b/3685/CH21/EX21.8/Ex21_8.sce new file mode 100644 index 000000000..20a017993 --- /dev/null +++ b/3685/CH21/EX21.8/Ex21_8.sce @@ -0,0 +1,23 @@ +
+clc
+// Given that
+Pc = 2.4 // Pressure in combustion chamber in MPa
+Tc = 3170 // Temperature in combustion chamber in K
+Pj = 55 // Atmospheric pressure in kPa
+Pe = 85 // Pressure at the exit of nozzle in kPa
+At = 0.06 // Area at the nozzle throat in m^2
+n_n = 0.91 // Nozzle efficiency
+Cd = 0.98 // Coefficient of discharge
+gama = 1.25 // Heat capacities ratio for gases
+R = 0.693 // Value of gas constant in kJ/kgK
+theta = 12 // Half angle of divergence in degree
+printf("\n Example 21.8\n")
+Vj = sqrt((2*gama*R*1000*Tc/(gama-1))*(1-(Pj/(Pc*1000))^((gama-1)/gama)))
+Vj_act = ((1+cosd(12))/2)*Vj*sqrt(n_n)
+m = At*Pc*(10^6)*((gama/(R*1000*Tc))*(2/(gama+1))^((gama+1)/(gama-1)))^(1/2)
+m_act = Cd*m
+Ae = m/(Pe*Vj)
+Ft = m*Vj+Ae*(Pe-Pj)*1000
+SIm = Ft/m_act
+printf("\n Thrust produced = %f kN,\n Specific impulse = %f Ns/kg",Ft*0.001,SIm)
+// The answers are given in the book contain calculation error.
diff --git a/3685/CH21/EX21.8/Ex21_8.txt b/3685/CH21/EX21.8/Ex21_8.txt new file mode 100644 index 000000000..eecd7d299 --- /dev/null +++ b/3685/CH21/EX21.8/Ex21_8.txt @@ -0,0 +1,5 @@ +
+ Example 21.8
+
+ Thrust produced = 218.178625 kN,
+ Specific impulse = 3482.180070 Ns/kg
\ No newline at end of file |