Question

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.

Answer #1

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

M1=1.2:0.01:5;

ratio =1+((2*y)/(y+1)*(M1.^2-1)); %Using the relation of normal
shock (P2/P1)

P2=ratio*P1; %pressure after the shock

plot(M1,P2);

xlabel('M1');

ylabel('P2(in KPa)');

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