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+//ques1
+//Compression of High-Speed Air in an Aircraft
+clear
+clc
+//(a) the stagnation pressure at the compressor inlet (diffuser exit) can be determined from Eq. 17–5 in book
+//state 1
+T1=255.7;//Temperature in K
+V1=250;//velocity in m/s
+Cp=1.005;//specifc heat at const pressure in kJ/kg/K
+T01=T1+V1^2/(2*Cp)/1000;//divide 1000 to convert it into K
+//now from eqn 17-5
+P1=54.05;//pressure in kPa
+
+k=1.4;
+P01=P1*(T01/T1)^(k/(k-1));
+printf('(a) Pressure P01 = %.2f kPa \n',P01);
+
+//(b) To determine the compressor work
+r=8//P02/P01
+T02=T01*r^(1-1/k);//Temperature in K
+//Disregarding potential energy changes and heat transfer, the compressor work per unit mass of air is determined from Eq. 17–8
+Win=Cp*(T02-T01);//Work input in kJ/kg
+printf(' (b) Work input = %.1f kJ/kg \n',Win);