Where k is the thermal conductivity of its material, A is the cross sectional area and T=T(x) is the temperature distribution. For a. T(x) = tan(x) sec(x) + sin(x²), k=0.7 and A= 10 find Q at x=T/3. b. T(x) 1 xcos(4x) +, find Q at x = T/2. -x (x2-cos(2x). x2 с. Т(х) — х d. T(x) find Q at x = T/4. — 100е 3х + In(4x), k3470, А3 0.01п and x— 1/3;
Where k is the thermal conductivity of its material, A is the cross sectional area and T=T(x) is the temperature distribution. For a. T(x) = tan(x) sec(x) + sin(x²), k=0.7 and A= 10 find Q at x=T/3. b. T(x) 1 xcos(4x) +, find Q at x = T/2. -x (x2-cos(2x). x2 с. Т(х) — х d. T(x) find Q at x = T/4. — 100е 3х + In(4x), k3470, А3 0.01п and x— 1/3;
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
answer (c) branch please
![Where k is the thermal conductivity of its material, A is the cross
sectional area and T=T(x) is the temperature distribution. For
tan(x) sec(x) + sin(x²), k=0.7 and A= 10 find Q at
а. Т(х)
x=T/3.
b. T(x) = Vxcos(4x) +, find Q at x = T/2.
= x (x2-cos(2x)), find Q at x = 1/4.
хcos(4x) +
с. Т(x) — х
d. T(x) = 100e-3x + In(4x), k=470, A= 0.01n and x= 1/3;](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F3c426995-fc3b-4a87-9159-e65b0b436848%2Fe1af6265-55fc-489c-bdef-fec7796fd8a1%2Fcmbdj77_processed.png&w=3840&q=75)
Transcribed Image Text:Where k is the thermal conductivity of its material, A is the cross
sectional area and T=T(x) is the temperature distribution. For
tan(x) sec(x) + sin(x²), k=0.7 and A= 10 find Q at
а. Т(х)
x=T/3.
b. T(x) = Vxcos(4x) +, find Q at x = T/2.
= x (x2-cos(2x)), find Q at x = 1/4.
хcos(4x) +
с. Т(x) — х
d. T(x) = 100e-3x + In(4x), k=470, A= 0.01n and x= 1/3;
![Task 2
The heat transfer rate of the rocket engine is given by:
dT
Q = -kA
dx](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F3c426995-fc3b-4a87-9159-e65b0b436848%2Fe1af6265-55fc-489c-bdef-fec7796fd8a1%2Ffi8keyg_processed.png&w=3840&q=75)
Transcribed Image Text:Task 2
The heat transfer rate of the rocket engine is given by:
dT
Q = -kA
dx
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