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1. The flow is considered compressible when the value of Mach number is.... (A) greater than unity (B) greater or equal to 0.3 (C) greater than 0.5 (D) less than 0.3 2. In c-d nozzle, when dA/dV is positive, then the flow is.... (A) subsonic (B) sonic (C) supersonic (D) incompressible 3. Along the adiabatic duct, the...... remains constant. (A) stagnation pressure (B) static pressure (C) static temperature (D) stagnation temperature 4. Across the normal shock wave, the gas velocity ...... (A) decreases↓ (B) increases ↑ (C) remains constant (D) varies randomly v2 (C) 2Cp (D) PV² 5. The dynamic temperature can be calculated from..... (A): M² 2Cp (B) -M² B 6. A supersonic flow with 38° oblique shock angle passes over a concave corner of angle 0=20°. Then, the free stream Mach number M₁ is.... (A) 2 (B) 5 7. Across the expansion waves, the ..... remains constant. (A) Mach number (B) stagnation pressure (C) 3 (C) gas velocity (D) 4 (D) temperature. (D) Pe=0 8. The maximal thrust of the rocket can be obtained when the exit pressure (Pe) is .... (A) Pe=Pa (B) Pe>Pa 9. In turbojet engine, the water can be injected..... (A) before the compressor (C) Pe

1. The flow is considered compressible when the value of Mach number is.... (A) greater than unity (B) greater or equal to 0.3 (C) greater than 0.5 (D) less than 0.3 2. In c-d nozzle, when dA/dV is positive, then the flow is.... (A) subsonic (B) sonic (C) supersonic (D) incompressible 3. Along the adiabatic duct, the...... remains constant. (A) stagnation pressure (B) static pressure (C) static temperature (D) stagnation temperature 4. Across the normal shock wave, the gas velocity ...... (A) decreases↓ (B) increases ↑ (C) remains constant (D) varies randomly v2 (C) 2Cp (D) PV² 5. The dynamic temperature can be calculated from..... (A): M² 2Cp (B) -M² B 6. A supersonic flow with 38° oblique shock angle passes over a concave corner of angle 0=20°. Then, the free stream Mach number M₁ is.... (A) 2 (B) 5 7. Across the expansion waves, the ..... remains constant. (A) Mach number (B) stagnation pressure (C) 3 (C) gas velocity (D) 4 (D) temperature. (D) Pe=0 8. The maximal thrust of the rocket can be obtained when the exit pressure (Pe) is .... (A) Pe=Pa (B) Pe>Pa 9. In turbojet engine, the water can be injected..... (A) before the compressor (C) Pe

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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1. The flow is considered compressible when the value of Mach number is.... (A) greater than unity (B) greater or equal to 0.3 (C) greater than 0.5 (D) less than 0.3 2. In c-d nozzle, when dA/dV is positive, then the flow is.... (A) subsonic (B) sonic (C) supersonic (D) incompressible 3. Along the adiabatic duct, the...... remains constant. (A) stagnation pressure (B) static pressure (C) static temperature (D) stagnation temperature 4. Across the normal shock wave, the gas velocity ...... (A) decreases↓ (B) increases ↑ (C) remains constant (D) varies randomly v2 (C) 2Cp (D) PV² 5. The dynamic temperature can be calculated from..... (A): M² 2Cp (B) -M² B 6. A supersonic flow with 38° oblique shock angle passes over a concave corner of angle 0=20°. Then, the free stream Mach number M₁ is.... (A) 2 (B) 5 7. Across the expansion waves, the ..... remains constant. (A) Mach number (B) stagnation pressure (C) 3 (C) gas velocity (D) 4 (D) temperature. (D) Pe=0 8. The maximal thrust of the rocket can be obtained when the exit pressure (Pe) is .... (A) Pe=Pa (B) Pe>Pa 9. In turbojet engine, the water can be injected..... (A) before the compressor (C) Pe<Pa (B)after the compressor (C)after the turbine (D) both (A) and (B) 10. The afterburning and the water injection are used to.... (A) increase the thrust for a short period (B)reduce the weight of the turbojet engine (C) cooling the turbine (D) both (A) and (B)
Transcribed Image Text:1. The flow is considered compressible when the value of Mach number is.... (A) greater than unity (B) greater or equal to 0.3 (C) greater than 0.5 (D) less than 0.3 2. In c-d nozzle, when dA/dV is positive, then the flow is.... (A) subsonic (B) sonic (C) supersonic (D) incompressible 3. Along the adiabatic duct, the...... remains constant. (A) stagnation pressure (B) static pressure (C) static temperature (D) stagnation temperature 4. Across the normal shock wave, the gas velocity ...... (A) decreases↓ (B) increases ↑ (C) remains constant (D) varies randomly v2 (C) 2Cp (D) PV² 5. The dynamic temperature can be calculated from..... (A): M² 2Cp (B) -M² B 6. A supersonic flow with 38° oblique shock angle passes over a concave corner of angle 0=20°. Then, the free stream Mach number M₁ is.... (A) 2 (B) 5 7. Across the expansion waves, the ..... remains constant. (A) Mach number (B) stagnation pressure (C) 3 (C) gas velocity (D) 4 (D) temperature. (D) Pe=0 8. The maximal thrust of the rocket can be obtained when the exit pressure (Pe) is .... (A) Pe=Pa (B) Pe>Pa 9. In turbojet engine, the water can be injected..... (A) before the compressor (C) Pe<Pa (B)after the compressor (C)after the turbine (D) both (A) and (B) 10. The afterburning and the water injection are used to.... (A) increase the thrust for a short period (B)reduce the weight of the turbojet engine (C) cooling the turbine (D) both (A) and (B)
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