The altitude h [ft] attained by an aircraft climbing from sea level at its maximum rate of climb [ft/min] is shown at four times t [min]. index, i: 1 2 3 4 ti [min]: h; [ft]: ! 10 20 30 40 5400 9000 11600 12800 Estimate the aircraft's rate of climb (dh/dt)3 when it is at an altitude of 11600 ft by the following techniques.

Advanced Engineering Mathematics
10th Edition
ISBN:9780470458365
Author:Erwin Kreyszig
Publisher:Erwin Kreyszig
Chapter2: Second-order Linear Odes
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The altitude h [ft] attained by an aircraft climbing from sea level at its maximum rate
of climb [ft/min] is shown at four times t [min]).
index, i:
2
3
4
t; [min]:
* 10
20
30
40
h; [ft]:
5400 9000
11600 12800
Estimate the aircraft's rate of climb (dh/dt)3 when it is at an altitude of 11600 ft by
the following techniques.
(a) Use a backward-difference formula with data at i equal to 2 and 3.
(b) Use a forward-difference formula with data at i equal to 3 and 4.
(c) Use a central-difference formula with data at i equal to 2 and 4.
(d) Develop and use a third-order difference formula with data at all values of i.
Transcribed Image Text:The altitude h [ft] attained by an aircraft climbing from sea level at its maximum rate of climb [ft/min] is shown at four times t [min]). index, i: 2 3 4 t; [min]: * 10 20 30 40 h; [ft]: 5400 9000 11600 12800 Estimate the aircraft's rate of climb (dh/dt)3 when it is at an altitude of 11600 ft by the following techniques. (a) Use a backward-difference formula with data at i equal to 2 and 3. (b) Use a forward-difference formula with data at i equal to 3 and 4. (c) Use a central-difference formula with data at i equal to 2 and 4. (d) Develop and use a third-order difference formula with data at all values of i.
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