The heat transfer rate of the rocket engine is given by: dT Q = -kA –dx 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=0/3.
The heat transfer rate of the rocket engine is given by: dT Q = -kA –dx 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=0/3.
Advanced Engineering Mathematics
10th Edition
ISBN:9780470458365
Author:Erwin Kreyszig
Publisher:Erwin Kreyszig
Chapter2: Second-order Linear Odes
Section: Chapter Questions
Problem 1RQ
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Transcribed Image Text:The heat transfer rate of the rocket engine is given by:
dT
Q = -kA – dx
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(x?), k=0.7 and A= 10 find Q at x=0/3.
1 b.
(x) = Vxco(4x) +
L find Q at x = 0/2.
2
(2) = x (x2-cos(2x)) find Q at x = 0/4.
с. Т
(х) —D х
d. T
(x) = 100e¬3× + In(4x), k=470, A= 0.010 and x= 1/3;
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