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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/EX21.4/Ex21_4.sce | |
| parent | b1f5c3f8d6671b4331cef1dcebdf63b7a43a3a2b (diff) | |
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initial commit / add all books
Diffstat (limited to '3685/CH21/EX21.4/Ex21_4.sce')
| -rw-r--r-- | 3685/CH21/EX21.4/Ex21_4.sce | 54 |
1 files changed, 54 insertions, 0 deletions
diff --git a/3685/CH21/EX21.4/Ex21_4.sce b/3685/CH21/EX21.4/Ex21_4.sce new file mode 100644 index 000000000..a560bdd2a --- /dev/null +++ b/3685/CH21/EX21.4/Ex21_4.sce @@ -0,0 +1,54 @@ +clc
+// Given that
+v = 800 // Speed of aircraft in km/h
+h = 10700 // Height of aircraft in m
+p0 = 0.24 // Pressure in bar
+t0 = -50 // Temperature in degree centigrade
+r_p = 10 // Compressor pressure ratio
+t03 = 1093 // Max cycle temperature in K
+n_ed = 0.9 // Entry duct efficiency
+n_c = 0.9 // Isentropic efficiency of compressure
+p_ = 0.14 // Stagnation pressure loss in combustion chamber in bar
+cv = 43.3 // Calorific value of fuel in MJ/kg
+n_C = 0.98 // Combustion efficiency
+n_t = 0.92 // Isentropic efficiency of turbine
+n_m = 0.98 // Mechanical efficiency of drive
+n_j = 0.92 // Jet pipe efficiency
+a = 0.08 // Nozzle outlet area in m^2
+Cp = 1.005 // Heat capacity of air in kJ/kgK
+gama = 1.4 // Ratio of heat capacities for air
+Cp_ = 1.15 // Heat capacity for gases in kJ/kgK
+gama_ = 1.333 // Ratio of heat capacities for gases
+printf("\n Example 21.4\n")
+KE = (1/2)*(v*5/18)^2
+tr = KE/(1000*Cp)
+t01 = tr + (273+t0)
+t01_s = (t0+273)+(n_ed*(t01-(t0+273)))
+p01 = p0*((t01_s/(t0+273))^(gama/(gama-1)))
+t02_s = t01*((r_p)^((gama-1)/gama))
+t02 = (t01) + (t02_s-t01)/n_c
+p02 = p01*r_p
+p03 = p02-p_
+t04 = t03 - (Cp*(t02-t01)/(Cp_*n_m))
+t04_s = t03-(t03-t04)/n_t
+p04 = p03/((t03/t04_s)^(gama_/(gama_-1)))
+p_cr = p04*((2/(gama_+1))^(gama_/(gama_-1)))
+t05 = t04*(2/(gama_+1))
+t05_s = t04-((t04-t05)/n_j)
+p05 = p04/((t04/t05_s)^(gama_/(gama_-1)))
+R = Cp_*(gama_-1)/gama_
+v5 = R*t05/(p05*100)
+Vj = sqrt(gama_*R*1000*t05)
+m = a*Vj/v5
+Mt = m*(Vj-v*(5/18))
+Pt = (p05-p0)*a*10^5
+Tt = Mt+Pt
+Q1 = m*(t03-t02)*Cp_
+m_f = Q1/(cv*1000*n_C)
+m_sf = m_f*1000/Tt
+printf("\n Total thrust developed = %f N,\n The specific fuel consumption = %f kg/kNs",Tt,m_sf)
+// The answers given in the book contain round off error.
+
+
+
+
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