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What is the ratio of flight speed to the exhaust velocity for maximum propulsion efficiency ?
What is the ratio of flight speed to the exhaust velocity for maximum propulsion efficiency ?
GATE

Kisan Kumar Asked on 2nd October 2019 in Propulsion.
- 1K views
- 1 answers
- 0 votes
The logarithmic decrement measured for a viscously damped single degree of freedom system is 0.125. What is the value of the damping factor in percent?
The logarithmic decrement measured for a viscously damped single degree of freedom system is 0.125. What is the value of …
GATE

Kisan Kumar Asked on 2nd October 2019 in Control system.
- 1K views
- 1 answers
- 0 votes
Find the radial component and tangential component of the fluid’s velocity.
A thin long circular pipe of 10 mm diameter has porous walls and spins at 60 rpm about its own …
GATE

Kisan Kumar Asked on 1st October 2019 in Fluid dynamics.
- 1K views
- 1 answers
- 0 votes
Poll When is the critical Mach number of an airfoil attained ?
The critical Mach number of an airfoil is attained when
airfoil

Airplane design

GATE

Kisan Kumar Asked on 1st October 2019 in Design.
- 724 views
- 1 answers
- 0 votes
Poll What is the lift coefficient?
For a symmetric airfoil,the lift coefficient for zero degree angle of attack is
airfoil

Airplane design

GATE

Kisan Kumar Asked on 30th September 2019 in Design.
- 743 views
- 1 answers
- 0 votes
Poll Where is the zero pitching moment for an aircraft in trimmed condition?
An aircraft in trimmed condition has zero pitching moment at
Aircraft performance

GATE

Kisan Kumar Asked on 30th September 2019 in Flight mechanics.
- 631 views
- 1 answers
- 0 votes
A rocket motor has a combustion chamber temperature of 2600 K and the products have molecular weight of 25g/mol and ratio of specific heats 1.2.The universal gas constant is 8314 J/kg-mol-K. What is the value of theoretical \(c^{*}\) in (m/s)?
A rocket motor has a combustion chamber temperature of 2600 K and the products have molecular weight of 25g/mol and …
GATE

rocket propulsion

Kisan Kumar Asked on 30th September 2019 in Rocket and Space propulsion.
- 1K views
- 1 answers
- 0 votes
An airfoil generates a lift of 80 N when operating in a free stream flow of 60 m/s. If the ambient pressure and temperature are 100 kPa and 290 K respectively ( specific gas constant is 287 J/kg-K), find the circulation on the airfoil.
An airfoil generates a lift of 80 N when operating in a free stream flow of 60 m/s. If the …
GATE

incompressible flow

Kisan Kumar Asked on 30th September 2019 in Aerodynamics.
- 1K views
- 1 answers
- 0 votes

What is the ratio of flight speed to the exhaust velocity for maximum propulsion efficiency ?

The logarithmic decrement measured for a viscously damped single degree of freedom system is 0.125. What is the value of the damping factor in percent?

Find the radial component and tangential component of the fluid’s velocity.

Poll When is the critical Mach number of an airfoil attained ?

Poll What is the lift coefficient?

Poll Where is the zero pitching moment for an aircraft in trimmed condition?

A rocket motor has a combustion chamber temperature of 2600 K and the products have molecular weight of 25g/mol and ratio of specific heats 1.2.The universal gas constant is 8314 J/kg-mol-K. What is the value of theoretical \(c^{*}\) in (m/s)?

An airfoil generates a lift of 80 N when operating in a free stream flow of 60 m/s. If the ambient pressure and temperature are 100 kPa and 290 K respectively ( specific gas constant is 287 J/kg-K), find the circulation on the airfoil.

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