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Kisan Kumar
Consider an incompressible two-dimensional viscous flow over a curved surface. Let the pressure distribution on the surface be $p(s)=2+sin\left ( \frac{\pi}{2}+s \right )\;N/m^2$ ,where $s$ is the distance along the curved surface from the leading edge. Find the distance from where the flow separates.
- GATE
- incompressible flow
on 30th December 2019 in Aerodynamics.
- 2K
- 1
- 0
Kisan Kumar
Poll The angular momentum about the centre of mass of the earth of an artificial satellite in a highly elliptical orbit is
- GATE
- satellite
on 12th November 2019 in Astrodynamics.
- 1K
- 0
- 0
Kisan Kumar
Poll The absolute ceiling of an aircraft is the altitude above which it
on 11th November 2019 in Flight mechanics.
- 965
- 0
- 0
Kisan Kumar
All the factors remaining constant, if the weight of an aircraft increases by $30 \%$ then the take off distance will increase by approximately.
on 10th November 2019 in Flight mechanics.
- 2K
- 1
- 0
Kisan Kumar
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.
- GATE
on 15th October 2019 in Aerodynamics.
- 2K
- 1
- 0
Kisan Kumar
Find the shock angle and the total temperature at point P.
- GATE
on 15th October 2019 in Aerodynamics.
- 2K
- 1
- 0
Kisan Kumar
Poll Prandtl’s lifting line theory.
- GATE
on 15th October 2019 in Aerodynamics.
- 1K
- 0
- 0
Kisan Kumar
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 $C_{L}$ .
- GATE
on 14th October 2019 in Flight mechanics.
- 2K
- 1
- 0
Kisan Kumar
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 ?
- GATE
on 14th October 2019 in Aerodynamics.
- 1K
- 1
- 0
Kisan Kumar
An elliptic orbit has its perigee at 400 km above the earth’s surface and apogee at 3400 km above the earth’s surface. For this orbit, what is the eccentricity and semi-major axis respectively.
- GATE
on 14th October 2019 in Space dynamics.
- 1K
- 1
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Poll The angular momentum about the centre of mass of the earth of an artificial satellite in a highly elliptical orbit is

Poll The absolute ceiling of an aircraft is the altitude above which it

All the factors remaining constant, if the weight of an aircraft increases by 30 \%30 \% then the take off distance will increase by approximately.

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.

Find the shock angle and the total temperature at point P.

Poll Prandtl’s lifting line theory.

Consider flow over a thin aerofoil at Mach number,M_{\infty}=0.5M_{\infty}=0.5 at an angle of attack of \alpha\alpha. Using the Prandtl-Glauert rule for compressibility correction find a formula for lift coefficient C_{L}C_{L}.

An elliptic orbit has its perigee at 400 km above the earth’s surface and apogee at 3400 km above the earth’s surface. For this orbit, what is the eccentricity and semi-major axis respectively.

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

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 $C_{L}$ .