1
1.2
1.3
1.4
A. 1
The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel
The stagnation conditions exist at the combustion chamber
The exit velocities of exhaust gases are much higher than those in jet engine
All of the above
The propulsive matter is caused to flow around the propelled body
Propulsive matter is ejected from within the propelled body
Its functioning does not depend on presence of air
All of the above
Atmosphere
Vacuum
Discharge nozzle
Back to the compressor
Centrifugal compressors deliver practically constant pressure over a considerable range of capacities
Axial flow compressors have a substantially constant delivery at variable pressures
Centrifugal compressors have a wider stable operating range than axial flow compressors
Axial flow compressors are bigger in diameter compared to centrifugal type
It is inefficient
It is bulky
It requires cooling water for its operation
None of the above
1 to 5 bar
5 to 8 bar
8 to 10 bar
10 to 15 bar
The compression ratio in each stage should be same
The intercooling should be perfect
The workdone in each stage should be same
All of the above
Throttle control
Clearance control
Blow off control
Any one of the above
Start-stop motor
Constant speed unloader
Relief valve
Variable speed
Closed cycle
Open cycle
Both of the above
Closed/open depending on other considerations
Atmosphere
Back to the compressor
Discharge nozzle
Vacuum
1 : 1.2
1 : 2
1 : 5
1 : 10
Reciprocating compressor
Centrifugal compressor
Axial flow compressor
Turbo compressor
One adiabatic, two isobaric, and one constant volume
Two adiabatic and two isobaric
Two adiabatic, one isobaric and one constant volume
One adiabatic, one isobaric and two constant volumes
The reciprocating compressors are best suited for high pressure and low volume capacity
The effect of clearance volume on power consumption is negligible for the same volume of discharge
Both (A) and (B)
None of these
Employing intercooler
By constantly cooling the cylinder
By running compressor at very slow speed
By insulating the cylinder
Increases the thermal efficiency
Increases the compressor work
Increases the turbine work
Decreases the thermal efficiency
Compression index
Compression ratio
Compressor efficiency
Mean effective pressure
Is self operating at zero flight speed
Is not self operating at zero flight speed
Requires no air for its operation
Produces a jet consisting of plasma
Increases as clearance volume increases
Decreases as clearance volume increases
Is independent of clearance volume
Increases as clearance volume decreases
Brayton or Atkinson cycle
Carnot cycle
Rankine cycle
Erricson cycle
Increase in net output but decrease in thermal efficiency
Increase in thermal efficiency but decrease in net output
Increase in both thermal efficiency and net output
Decrease in both thermal efficiency and net output
Has no effect on
Decreases
Increases
None of these
Before intercooler
After intercooler
After receiver
Between after-cooler and air receiver
Decreasing the compression work
Increasing the compression work
Increasing the turbine work
Both (A) and (C) above
In one cylinder
In two cylinders
In a single cylinder on both sides of the piston
In two cylinders on both sides of the piston
Standard air
Free air
Compressed air
Compressed air at delivery pressure
Decrease
Increase
Remain same
Does not change
D₁/D₂ = (p₁ p₃)1/2
D₁/D₂ = (p₁/p₃)1/4
D₁/D₂ = (p₁ p₃)1/4
D₁/D₂ = (p₃/p₁)1/4
10 bar
20 bar
30 bar
50 bar