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Advanced Engineering Mathematics with MATLAB 5th Edition – Duffy Solutions Manual | Complete Solved Problems + MATLAB Applications PDF

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This Solutions Manual for Advanced Engineering Mathematics with MATLAB (5th Edition) by Dean G. Duffy provides comprehensive, step-by-step solutions to all textbook problems, examples, and exercises. It integrates analytical techniques and MATLAB computational methods, helping students understand both the theoretical and applied aspects of engineering mathematics. Topics include linear algebra, differential equations, vector calculus, Fourier analysis, Laplace transforms, complex variables, and numerical methods. Each solution demonstrates clear mathematical reasoning and MATLAB implementation examples, making this manual ideal for students and instructors seeking to master both manual and computational problem-solving. Perfect for courses in Applied Mathematics, Electrical and Mechanical Engineering, and Computational Modeling. ① KEY DETAILS Edition: 5th Edition Author: Dean G. Duffy Type: Complete Solutions Manual (Merged PDF) Includes: Analytical derivations and MATLAB-based solutions Ideal for: Engineering, Applied Math, and Computational Sc

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Institution
Aircraft Structures For Engineering
Course
Aircraft Structures for Engineering

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@SOLUTIONSSTUDY




All Chapters Covered




SOLUTIONS

,Table of Contents
Chapter 1: First-Order Ordinary Differential Equations
1 Chapter 2: Higher-Order Ordinary Differential
Equations Chapter 3: Linear Algebra
Chapter 4: Vector Calculus
Chapter 5: Fourier Series
Chapter 6: The Fourier Transform
Chapter 7: The Laplace Transform
Chapter 8: The Wave Equation
Chapter 9: The Heat Equation
Chapter 10: Laplace’s Equation
Chapter 11: The Sturm-Liouville Problem
Chapter 12: Special Functions
Appendix A: Derivation of the Laplacian in Polar Coordinates
Appendix B: Derivation of the Laplacian in Spherical Polar
Coordinates

, @SOLUTIONSSTUDY




Solution Manual
Section 1.1

1. first-order, linear 2. first-order, nonlinear
3. first-order, nonlinear 4. third-order, linear
5. second-order, linear 6. first-order, nonlinear
7. third-order, nonlinear 8. second-order, linear
9. second-order, nonlinear 10. first-order, nonlinear
11. first-order, nonlinear 12. second-order, nonlinear
13. first-order, nonlinear 14. third-order, linear
15. second-order, nonlinear 16. third-order, nonlinear

Section 1.2

1. Because the differential equation can be rewritten e−y dy = xdx, integra-
tion immediately gives —e−y = 1 x2 — C, or y = — ln(C — x2/2).
2

2. Separating variables, we have that dx/(1 + x2) = dy/(1 + y2). Integrating
this equation, we find that tan −1(x) −1
— tan (y) = tan(C), or (x — y)/(1+xy) =
C.

3. Because the differential equation can be rewritten ln(x)dx/x = y dy, inte-
gration immediately gives 1 ln 2(x) + C = 1 y2, or y2(x) — ln 2(x) = 2C.
2 2

4. Because the differential equation can be rewritten y2 dy = (x + x3 ) dx,
integration immediately gives y3(x)/3 = x2 /2 + x4/4 + C.

5.2 Because the differential equation can1 be rewritten y dy/(2+y2) = xdx/(1+
x ), integration immediately gives ln(2 + y2) = 1 ln(1 + x2) + 1 ln(C), or
2 2 2
2 + y2(x) = C(1 + x2).

6. Because the differential equation can be rewritten dy/y1/3 = x1/3 dx,
3/2
integration immediately gives
2
y =4 3 x4/3 +2 3 C, or y(x) = 21 x4/3 + C .
3 2/3



1

, @SOLUTIONSSTUDY


2 Advanced Engineering Mathematics with MATLAB

7. Because the differential equation can be rewritten e−y dy = ex dx, integra-
tion immediately gives —e−y = ex — C, or y(x) = — ln(C — ex).
8. Because the differential equation can be rewritten dy/(y2 + 1) = (x3 +
5) dx, integration immediately gives tan −1(y) = 1 x4 + 5x + C, or y(x)
=
4
tan 14 x4 + 5x + C .

9. Because the differential equation can be rewritten y2 dy/(b — ay3 ) = dt,
integration immediately gives ln[b — ay 3] yy0 = —3at, or (ay 3 — b)/(ay03 — b) =
e−3at.

10. Because the differential equation can be written du/u = dx/x2 , integra-
tion immediately gives u = Ce−1/x or y(x) = x + Ce−1/x.

11. From the hydrostatic equation and ideal gas law, dp/p = — g dz/(RT ).
Substituting for T (z),
dp g
=— dz.
p R(T0 — Γz)
Integrating from 0 to z,

p(z) g T0 — p(z) T0 — Γz g/(RΓ)
ln = ln Γz , or = .
p0 RΓ p0 T0
T0


12. For 0 < z < H, we simply use the previous problem. At z = H,
the pressure is
T0 — ΓH g/(RΓ)
p(H) = p0 .
T0
Then we follow the example in the text for an isothermal atmosphere for
z ≥ H.

13. Separating variables, we find that
dV dV R dV dt
2
= — =— .
V + RV /S V S(1 + RV/S) RC

Integration yields

V t
ln =— + ln(C).
1 + RV/S RC
Upon applying the initial conditions,

V0 RV0/S
V (t) = e−t/(RC) + e−t/(RC)V (t).
1 + RV0/S 1 + RV0/S

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Institution
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Aircraft Structures for Engineering

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