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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 ( … Kisan Kumar Asked on 30th December 2019 in • 1K 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 … Kisan Kumar Asked on 12th November 2019 in • 840 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 Kisan Kumar Asked on 11th November 2019 in • 696 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 …

Kisan Kumar Asked on 10th November 2019 in
• 1K 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 …

Kisan Kumar Asked on 15th October 2019 in
• 2K views

Consider an inviscid, adiabatic flow of air at free stream Mach number $$M_{\infty}=2$$, across a compression corner $$\left ( \theta … Kisan Kumar Asked on 15th October 2019 in • 1K 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? Kisan Kumar Asked on 15th October 2019 in • 765 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 …

Kisan Kumar Asked on 14th October 2019 in
• 1K 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 ( …

Kisan Kumar Asked on 14th October 2019 in
• 1K views