At a given instant of time, two pressure waves, each moving at the speed of sound, emitted by a point source moving with a constant velocity in a fluid in at rest are shown in figure QB2. Determine the Mach number involved and indicate with a sketch the instantaneous location of the point source.
At a given instant of time, two pressure waves, each moving at the speed of sound, emitted by a point source moving with a constant velocity in a fluid in at rest are shown in figure QB2. Determine the Mach number involved and indicate with a sketch the instantaneous location of the point source.
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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![Question B2
a) At a given instant of time, two pressure waves, each moving at the speed of sound, emitted by a
point source moving with a constant velocity in a fluid in at rest are shown in figure QB2.
Determine the Mach number involved and indicate with a sketch the instantaneous location of the
point source.
R=5 cm
12 cm
Figure QB2
R=24 cm
[8 Marks]
b) The gas velocity across a normal shock wave decreases from 480 m/s to 160 m/s. If the pressure and
density upstream of the shock are 62 kPa and 1.5 kg/m ³, find the pressure and density downstream
of the shock and the specific heat ratio of the gas.
c) An aircraft is in supersonic flight at 11 km altitude on a standard day. The true air speed of the plane
is 695 m/s. Calculate the flight Mach number of the aircraft. A total head tube is attached to the
plane is used to sense stagnation pressure which is converted to flight Mach number by an on-board
computer. However, the computer programme has ignored the normal shock wave that stands in
front of the total head tube and assumed isentropic flow. Evaluate the pressure sensed by the total
head tube. Determine the erroneous air speed calculated by the computer programme. The
atmospheric pressure and temperature at 11 km altitude are 0.23 bar and 216 K respectively.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F97169250-b02b-4db2-9610-24afc15ffb22%2Ffa57b2fa-713f-4a43-bb4a-ad6deac7c9a3%2Fk0rfz56_processed.jpeg&w=3840&q=75)
Transcribed Image Text:Question B2
a) At a given instant of time, two pressure waves, each moving at the speed of sound, emitted by a
point source moving with a constant velocity in a fluid in at rest are shown in figure QB2.
Determine the Mach number involved and indicate with a sketch the instantaneous location of the
point source.
R=5 cm
12 cm
Figure QB2
R=24 cm
[8 Marks]
b) The gas velocity across a normal shock wave decreases from 480 m/s to 160 m/s. If the pressure and
density upstream of the shock are 62 kPa and 1.5 kg/m ³, find the pressure and density downstream
of the shock and the specific heat ratio of the gas.
c) An aircraft is in supersonic flight at 11 km altitude on a standard day. The true air speed of the plane
is 695 m/s. Calculate the flight Mach number of the aircraft. A total head tube is attached to the
plane is used to sense stagnation pressure which is converted to flight Mach number by an on-board
computer. However, the computer programme has ignored the normal shock wave that stands in
front of the total head tube and assumed isentropic flow. Evaluate the pressure sensed by the total
head tube. Determine the erroneous air speed calculated by the computer programme. The
atmospheric pressure and temperature at 11 km altitude are 0.23 bar and 216 K respectively.
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