... 5.37 Show that an airplane can travel in a constant-velocity glide (i.e., having thrust FT = 0) if it is pointed downward by a negative angle Oglide below the horizontal axis with a = 0 if Oglide - arctan (5.44) %3D
... 5.37 Show that an airplane can travel in a constant-velocity glide (i.e., having thrust FT = 0) if it is pointed downward by a negative angle Oglide below the horizontal axis with a = 0 if Oglide - arctan (5.44) %3D
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5.37 and 5.39 only!!!!
Transcribed Image Text:cos(0) + sin(0).
(5.43)
Using this equation, create a plot of Q vs. 7 for 0 = 0°,10°, 20°,..., 110° (for a
total of 12 curves) for 0 < n < 1.0. What is significantly different between the
curves for which 0 < 90° and the curves for which 0 > 90°? For what range of
values of n is it impossible to fly a plane with 0 = 100°? (In other words, what
range of values of 7 result in Q < 0?)
... 5.37 Show that an airplane can travel in a constant-velocity glide (i.e., having
thrust FT =
horizontal axis with a = 0 if
0) if it is pointed downward by a negative angle Oglide below the
ch
ft
Oglide = - arctan
(5.44)
Ph
and
res
... 5.38 An airplane with a maximum lift-to-drag ratio of 3.5 enters into a glide
while at an altitude of 11,000 ft. How far can it travel in this glide?
(a
5.39 Calculate the maximum weight a plane can have during take-off if the
angle of attack must be between 1.0° and 9.0° (to have an effective take-off but
also ensure passenger comfort), 0 = 9.0°, the lift-to-drag ratio must be between
1.00 and 5.00, and the plane has a maximum thrust of 35000. lb. Should you
round this answer up or down?
(b)
![.. 5.35 Show that, for the case 0, a = 0, the results of
through (5.29)] reduce to the results for cruising flight [Eqs.
(5.27)
0).
in the
... 5.36 The results of Section 5.4 can be simplified if the plane
direction that it is pointing-i.e., if a = 0. Show that, for a = 0, u
lift-to-drag ratio n, and the thrust-to-weight ratio Q are related by the equation
de 0, the
1
· cos(0) + sin(0).
(5.43)
Q =
Using this equation, create a plot of Q vs. n for 0 = 0°,10°, 20°,., 110° (for a
total of 12 curves) for 0 < n < 1.0. What is significantly different between the
curves for which 0 < 90° and the curves for which 0 > 90°? For what range of
values of 7 is it impossible to fly a plane with 0 = 100°? (In other words, what
range of values of n result in Q < 0?)
of
be
... 5.37 Show that an airplane can travel in a constant-velocity glide (i.e., having
thrust FT = 0) if it is pointed downward by a negative angle 0glide below the
horizontal axis with a = 0 if
che
ft/=
Phy-
Oglide = - arctan
(5.44)
and
resp
... 5.38 An airplane with a maximum lift-to-drag ratio of 3.5 enters into a glide
while at an altitude of 11,000 ft. How far can it travel in this glide?
(a)
5.39 Calculate the maximum weight a plane can have during take-off if the
angle of attack must be between 1.0° and 9.0° (to have an effective take-off but
also ensure passenger comfort), 0 = 9.0°, the lift-to-drag ratio must be between
1.00 and 5.00, and the plane has a maximum thrust of 35000. 1b. Should you
round this answer up or down?
(b)
(c)](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2Fd2e6bca0-5751-4e3b-9150-515606817feb%2Fa61783f3-8a8a-40c6-aa6b-fa179e7653f8%2F6ho7wfi_processed.jpeg&w=3840&q=75)
Transcribed Image Text:.. 5.35 Show that, for the case 0, a = 0, the results of
through (5.29)] reduce to the results for cruising flight [Eqs.
(5.27)
0).
in the
... 5.36 The results of Section 5.4 can be simplified if the plane
direction that it is pointing-i.e., if a = 0. Show that, for a = 0, u
lift-to-drag ratio n, and the thrust-to-weight ratio Q are related by the equation
de 0, the
1
· cos(0) + sin(0).
(5.43)
Q =
Using this equation, create a plot of Q vs. n for 0 = 0°,10°, 20°,., 110° (for a
total of 12 curves) for 0 < n < 1.0. What is significantly different between the
curves for which 0 < 90° and the curves for which 0 > 90°? For what range of
values of 7 is it impossible to fly a plane with 0 = 100°? (In other words, what
range of values of n result in Q < 0?)
of
be
... 5.37 Show that an airplane can travel in a constant-velocity glide (i.e., having
thrust FT = 0) if it is pointed downward by a negative angle 0glide below the
horizontal axis with a = 0 if
che
ft/=
Phy-
Oglide = - arctan
(5.44)
and
resp
... 5.38 An airplane with a maximum lift-to-drag ratio of 3.5 enters into a glide
while at an altitude of 11,000 ft. How far can it travel in this glide?
(a)
5.39 Calculate the maximum weight a plane can have during take-off if the
angle of attack must be between 1.0° and 9.0° (to have an effective take-off but
also ensure passenger comfort), 0 = 9.0°, the lift-to-drag ratio must be between
1.00 and 5.00, and the plane has a maximum thrust of 35000. 1b. Should you
round this answer up or down?
(b)
(c)
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