Unformatted text preview: Increment
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
p_stat=P0/(A)^(gamma/(gamma-1)) /B; %Static pressure
%Pressure ratio 1 across oblique shock
%Pressure ratio from Oblique shock calculations
%Pressure ratio 2
%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)))
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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This homework help was uploaded on 03/31/2014 for the course AAE 334 taught by Professor Collicott during the Spring '09 term at Purdue.
- Spring '09