Solutions for Fundamentals of Aerodynamics, 7th Edition by Anderson

Fundamentals of Aerodynamics
7th Edition by John Anderson



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,Table of Contents are given below


Chapter 1: Aerodynamics: Some Introductory Thoughts
Chapter 2: Aerodynamics: Some Fundamental Principles and Equations
Chapter 3: Fundamentals of Inviscid, Incompressible Flow
Chapter 4: Incompressible Flow over Airfoils
Chapter 5: Incompressible Flow over Finite Wings
Chapter 6: Three-Dimensional Incompressible Flow
Chapter 7: Compressible Flow: Some Preliminary Aspects
Chapter 8: Normal Shock Waves and Related Topics
Chapter 9: Oblique Shock and Expansion Waves
Chapter 10: Compressible Flow Through Nozzles, Diffusers, and Wind Tunnels
Chapter 11: Subsonic Compressible Flow over Airfoils: Linear Theory
Chapter 12: Linearized Supersonic Flow
Chapter 13: Introduction to Numerical Techniques for Nonlinear Supersonic
Flow
Chapter 13: Introduction to Numerical Techniques for Nonlinear Supersonic
Flow
Chapter 14: Elements of Hypersonic Flow
Chapter 15: Introduction to the Fundamental Principles and Equations of Viscous
Flow
Chapter 16: A Special Case: Couette Flow
Chapter 17: Introduction to Boundary Layers
Chapter 18: Laminar Boundary Layers
Chapter 19: Turbulent Boundary Layers

,Solutions Manual organized in reverse order, with the last chapter displayed
first, to ensure that all chapters are included in this document.

CHAPTER 19

19.1 1 mi/hr  0.4471 m/sec
 mi   0.4471 m/sec 
V  141     63.04 m/sec
 hr   1 mi/hr 

 V c (1.23)(63.04)(1.6)
Rec    6.93  106
 1.7894  105

1.328 1.328
(a) Cf    5.04  104
Rec 6.93  106


Nothing that drag exist on both the bottom and top surfaces, we have


Df  2 q S Cf  2( 1 2)(1.23)(63.04)2 (9.75)(1.6) 5.04  104  38.4 N
0.074 0.074
(b) Cf    3.17  103
 
1/5 1/5
Rec 6.93  106

 Cf turb 3.17  103
Df  (38.4)  (38.4)  241.5 N
 Cf lam 5.04  104

Note that turbulent skin friction is 6.28 times larger than the laminar value.


5.0x (5.0)(1.6)
19.2 (a)    3.04  103 m  0.304 cm
Re x 6.93  106
0.37x (0.37)(1.6)
(b)    2.54  102 m  2.54 cm
 
1/5 1/5
Re x 6.93  106



19.3




q  1
2 (1.23)(63.04)2  2444 N/m2



162

,  V  x1  x 0 
Rec  5  105



 x1  x 0  
5  105 

 
5  105 1.7894  105 
 0.1154 m
 V (1.23)(63.04)

Laminar drag on  x1  x0 :

1.328
Cf   1.878  103
5  10 5




Df  q S Cf  (2444)(0.1154)(9.75) 1.878  103  5.16 N 
Turbulent drag on  x1  x0 :

0.074
Cf   5.36  103
5  10 
1/5
5



 5.36  103 
Df   3 
5.16  14.73 N
 1.878  10 

From Prob.19.1, the turbulent drag on  x2  x 0  was 241.5 N. Hence,

Turbulent drag on  x 2  x1   241.5  14.73  226.8 N

Total skin friction drag   Laminar drag on  x1  x 0    Turbulent drag on  x 2  x1 

 5.16  226.8  232 N


19.4 At standard sea level:   0.002377 slug/ft

T  519R

a    RT  (1.4)(1716)(519)  1117 ft/sec




163