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Consider an incompressible two-dimensional viscous flow over a curved surface. Let the pressure distribution on the surface be $$p(s)=2+sin\left ( … Asked on 30th December 2019 in • 820 views • 1 answers • 0 votes • ## PollThe angular momentum about the centre of mass of the earth of an artificial satellite in a highly elliptical orbit is The angular momentum about the centre of mass of the earth of an artificial satellite in a highly elliptical orbit … Asked on 12th November 2019 in • 577 views • 2 answers • 0 votes • ## PollThe absolute ceiling of an aircraft is the altitude above which it The absolute ceiling of an aircraft is the altitude above which it Asked on 11th November 2019 in • 492 views • 2 answers • 0 votes • ## All the factors remaining constant, if the weight of an aircraft increases by \(30 \%$$ then the take off distance will increase by approximately.

All the factors remaining constant, if the weight of an aircraft increases by $$30 \%$$ then the take off distance …

Asked on 10th November 2019 in
• 907 views
• ## Consider a steady two-dimensional zero pressure gradient laminar flow of air over a flat plate as shown below. Find the ratio of displacement thickness to momentum thickness of the boundary layer at a distance of 2m from the leading edge.

Consider a steady two-dimensional zero pressure gradient laminar flow of air over a flat plate as shown below. The free …

Asked on 15th October 2019 in
• 1K views

Consider an inviscid, adiabatic flow of air at free stream Mach number $$M_{\infty}=2$$, across a compression corner $$\left ( \theta … Asked on 15th October 2019 in • 797 views • 1 answers • 0 votes • ## PollPrandtl’s lifting line theory. In the context of prandtl’s lifting line theory for a finite wing,which of the following combinations of statement is true? Asked on 15th October 2019 in • 528 views • 2 answers • 0 votes • ## Consider flow over a thin aerofoil at Mach number,\(M_{\infty}=0.5$$ at an angle of attack of $$\alpha$$. Using the Prandtl-Glauert rule for compressibility correction find a formula for lift coefficient $$C_{L}$$.

Consider flow over a thin aerofoil at Mach number, $$M_{\infty}=0.5$$ at an angle of attack of $$\alpha$$. Using the Prandtl-Glauert …

Asked on 14th October 2019 in
• 869 views
• ## 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 $$\left ( \theta =20^{\circ} \right )$$. Assume air to be calorically perfect with $$\gamma =1.4$$. What is the Mach number $$M_{2}$$, downstream of the expansion corner ?

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 ( …

Asked on 14th October 2019 in
• 773 views