1 files changed, 52 insertions, 0 deletions
diff --git a/2870/CH17/EX17.16/Ex17_16.sce b/2870/CH17/EX17.16/Ex17_16.sce
new file mode 100755
index 000000000..b868f27ff
--- /dev/null
+++ b/2870/CH17/EX17.16/Ex17_16.sce
@@ -0,0 +1,52 @@
+clc;clear;
+//Example 17.16
+
+//given data
+P01=2*1000;//factor of 1000 to convert MPa to kPa
+T1=400;
+V1=0;//negligible
+nN=0.93;
+m=2.5;
+P2=300;
+
+//calculations
+
+//part - a
+P201=P2/P01;
+//critical pressure ratio at this values is 0.546
+Pt=0.546*P01;
+//at inlet
+h1=3248.4;
+h01=h1;
+s1=7.1292;
+//at throat
+st=s1;
+ht=3076.8;
+vt=0.24196;
+Vt=sqrt(2*(h01-ht)*1000);//factor of 1000 to convert kJ to J
+At=m*vt/Vt;
+//at state 2s
+s2s=s1;
+h2s=2783.6;
+//nN = (h01 - h2)/ (h01 - h2s)
+h2=h01-nN*(h01-h2s);
+//at P2 and h2
+v2=0.67723;
+s2=7.2019;
+V2=sqrt(2*(h01-h2)*1000);//factor of 1000 to convert kJ to J
+A2=m*v2/V2;
+disp((At*10000),'throat area in cm^2');
+disp((A2*10000),'exit area in cm^2');
+
+//part - b
+// at st=7.1292
+//pressures of 1.115 and 1.065 MPa
+//c calculated using tables
+c=sqrt((1115-1065)/(1/0.23776 - 1/0.24633)*1000);//factor of 1000 to convert kPa to Pa
+Ma=Vt/c;
+disp(Ma,'the Mach number at the throat');
+// at s2=7.2019
+//pressures of 325 and 275 kPa
+c=sqrt((325-276)/(1/0.63596 - 1/0.72245)*1000);//factor of 1000 to convert kPa to Pa
+Ma=V2/c;
+disp(Ma,'the Mach number at the nozzle exit')