Need ASAP. Thank you! 1. The angle of attack (?) of a wing-body combination varies with its lift  coefficient ?? as follows: a

Advanced Engineering Mathematics
10th Edition
ISBN:9780470458365
Author:Erwin Kreyszig
Publisher:Erwin Kreyszig
Chapter2: Second-order Linear Odes
Section: Chapter Questions
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Need ASAP. Thank you!

1. The angle of attack (?) of a wing-body combination varies with its lift 
coefficient ?? as follows:

a 2.5 5.0 7.5
CL 0.17 0.13 0.44


a) Use central difference (CD) of the Taylor Series to calculate ???/??.
b) Combine Taylor Series Expansions (BWD and FWD) with Cramer’s Rule to 
determine the 1st derivative (??/???).
c) Calculate ??/???
from (a) and compare the result with that from (b)

1. The angle of attack (a) of a wing-body combination varies with its lift
coefficient C, as follows:
a
2.5
5.0
7.5
CL 0.17 0.31 0.44
a) Use central difference (CD) of the Taylor Series to calculate dC1/da.
b) Combine Taylor Series Expansions (BWD and FWD) with Cramer's Rule to
determine the 1st derivative (da/dCL).
c) Calculate da/dC, from (a) and compare the result with that from (b)
Transcribed Image Text:1. The angle of attack (a) of a wing-body combination varies with its lift coefficient C, as follows: a 2.5 5.0 7.5 CL 0.17 0.31 0.44 a) Use central difference (CD) of the Taylor Series to calculate dC1/da. b) Combine Taylor Series Expansions (BWD and FWD) with Cramer's Rule to determine the 1st derivative (da/dCL). c) Calculate da/dC, from (a) and compare the result with that from (b)
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