increment m till differs from by a specified

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Unformatted text preview: Increment gamma=1.4; theta=30*pi/180; %Wedge angle P0=25000; %Total pressure measured by the Pitot probe Pw=11000; %Static pressure on the surface of the wedge4 %Rayleigh Pitot Formula A=(gamma+1)^2*M^2 /(4*gamma*M^2-2*(gamma-1)); B=(1-gamma+2*gamma*M^2)/(gamma+1); p_stat=P0/(A)^(gamma/(gamma-1)) /B; %Static pressure %Pressure ratio 1 across oblique shock p_ratio1=Pw/p_stat; %Pressure ratio from Oblique shock calculations outs=obshk(gamma,M,theta,1); %Pressure ratio 2 p_ratio2=outs(5); %Iterate if the pressure ratio differ by a specified tolerance' %or if the output from the oblique shock calculations is a NaN %due to a small Mach number appearing in the iterations. while or((abs(p_ratio2-p_ratio1)>0.001*p_ratio1), (isnan(p_ratio2))) M=M+dM; A=(gamma+1)^2*M^2 /(4*gamma*M^2-2*(gamma-1)); B=(1-gamma+2*gamma*M^2)/(gamma+1); p_stat=P0/(A)^(gamma/(gamma-1)) /B; p_ratio1=Pw/p_stat; outs=obshk(gamma,M,theta,1); p_ratio2=outs(5); end disp('M') disp(M) The resulting Mach number is The freestream temperature and free stream pressure can be calculated using standard isentropic relations and the Rayleigh Pitot tube formula. The free stream Pressure is given by [ With , and ( ) ( ) [ , we find The velocity of the aircraft is therefore √ √ From Appendix D, we find the interpolated value for the altitude to be...
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