- (A) turbo-jet engine
- (B) ram-jet engine
- (C) propellers
- (D) rockets
- (E) hydraulic jet propulsion
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- (A) higher at ground
- (B) higher at high altitudes
- (C) same at all altitudes
- (D) higher at high speed
- (E) lower at low speed
- (A) gases
- (B) solids
- (C) liquid
- (D) plasma
- (E) highly heated atmospheric air
- (A) 2500°C
- (B) 2000°C
- (C) 1500°C
- (D) 1000°C
- (E) 700°C
- (A) high thermal efficiency
- (B) reduction in compressor work
- (C) decrease of heat loss in exhaust
- (D) maximum work output
- (E) none of the above
- (A) increases thermal efficiency
- (B) allows high compression ratio
- (C) decreases heat loss is exhaust
- (D) allows operation at very high altitudes
- (E) permits high moisture content fuel to be used
- (A) increase temperature
- (B) reduce turbine size
- (C) increase power output
- (D) increase speed
- (E) increase pressure ratio
- (A) both forward and return strokes
- (B) forward stroke
- (C) return stroke
- (D) none of these
- (A) atmosphere
- (B) back to the compressor
- (C) discharge nozzle
- (D) vacuum
- (E) none of the above
- (A) Vi=V0B
- (B) Vt>V0
- (C) U,<V0
- (D) V,= U0
- (E) Vri=Vm
