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# Performance of Ramjet Engines Jet Aircraft Propulsion IT & Software Notes | EduRev

## IT & Software : Performance of Ramjet Engines Jet Aircraft Propulsion IT & Software Notes | EduRev

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1
Lecture 40
Page 2

1
Lecture 40
2
Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect 40
Performance of
Ramjet Engines
Page 3

1
Lecture 40
2
Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect 40
Performance of
Ramjet Engines
3
Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect 40
Ramjet Engine Thermodynamic cycle
Page 4

1
Lecture 40
2
Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect 40
Performance of
Ramjet Engines
3
Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect 40
Ramjet Engine Thermodynamic cycle
4
Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect 40
Performance Parameters
Thrust : Ramjet engine thrust is defined as the net
change in total momentum as the working fluid
passes through the engine.
The general expression for thrust,
F = ?(C
4
-C
1
) + A
e.
(P
e
- P
a
)
where P
e
and P
a
are the engine exit and
ambient static pressures respectively
Page 5

1
Lecture 40
2
Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect 40
Performance of
Ramjet Engines
3
Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect 40
Ramjet Engine Thermodynamic cycle
4
Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect 40
Performance Parameters
Thrust : Ramjet engine thrust is defined as the net
change in total momentum as the working fluid
passes through the engine.
The general expression for thrust,
F = ?(C
4
-C
1
) + A
e.
(P
e
- P
a
)
where P
e
and P
a
are the engine exit and
ambient static pressures respectively
5
Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect 40
The general thrust equation may be modified to
include fuel mass flow and then may be rearranged
by substituting the mass flow term from the
continuity condition,
1
. . . 1 1
e e
a ea
a a
Vp
F V A m Ap
Vp
?
? ? ??
= -+ -
? ? ??
? ? ??
Where,                 , f=fuel/air ratio,            and
A
1
= Area of free stream air entering the engine
1 mf = +
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