Plot the variation of Mach number and static pressure as a supersonic airflow goes through a normal shock. The Mach number of the approaching flow varies between 1.2 to 5 (use ?M=0.01 for the incremental changes in MATLAB), and the static pressure before the shock is 100 kPa. Develop a short MATLAB code.
Show i assume here the flow is same and ...also i am assuming that all normal shock relation are known...
so the relation for pressure is given as -
figure is given in the plot below .
Matlab Code is given as following -
y=1.4; %flow coefficent
P1=100; %%presuree before the shock
ratio =1+((2*y)/(y+1)*(M1.^2-1)); %Using the relation of normal shock (P2/P1)
P2=ratio*P1; %pressure after the shock
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