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Consider an inviscid, adiabatic flow of air at free stream Mach number M_{\infty}=2, across a compression corner \(\left ( \theta …
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In the context of prandtl’s lifting line theory for a finite wing,which of the following combinations of statement is true?
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Consider the inviscid,adiabatic flow of air at free stream conditions M_{1}=2,P_{1}=1\;atm and T_{1}=288\;K around a sharp expansion corner \(\left ( …
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A low speed wind tunnel has a contraction ratio of 14:1 and the cross-sectional area of the test section is …
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An oblique shock wave with a wave angle \beta is generated from a wedge angle of \theta.What is the ratio …
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An airfoil generates a lift of 80 N when operating in a free stream flow of 60 m/s. If the …
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Write a Matlab code for a point vortex.
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Write a Matlab code for a doublet at the origin.
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Write a matlab code for a uniform flow flowing in X – direction having a constant velocity depicting equipotential lines …
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Write a MATLAB code for a source flow at the origin.
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