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=r/3. b. T(x) = /xcos(4x) +÷, find Q at x = 1/2. c. T(x) = x (**-cos(2x). find Q at x = 1/4. d. T(x) = 100e¬3x + In(4x), k=470, A= 0.01r and x= 1/3; %3D

Advanced Engineering Mathematics
10th Edition
ISBN:9780470458365
Author:Erwin Kreyszig
Publisher:Erwin Kreyszig
Chapter2: Second-order Linear Odes
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Task 2
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=n/3.
b. T(x) = /xcos(4x)+, find Q at x = T/2.
%3D
%3D
(x²-cos(2x)). find Q at x = r/4.
с. Т(x) %3D х
d. T(x) = 100e¬3x + In(4x), k=470, A= 0.01r and x= 1/3;
Transcribed Image Text:Task 2 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=n/3. b. T(x) = /xcos(4x)+, find Q at x = T/2. %3D %3D (x²-cos(2x)). find Q at x = r/4. с. Т(x) %3D х d. T(x) = 100e¬3x + In(4x), k=470, A= 0.01r and x= 1/3;
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