Solutions Manual for Aircraft Performance: An Engineering Approach, 2nd Edition by Mohammad H. Sadraey – Complete Chapters Step-by-Step Answers

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,Aircraft Performance, An Engineering Approach 2nd Edition by Sadraey All Chapters 1 to 10




Table of Contents
1. Atmosphere.

2. Eqụations of Motion.

3. Drag Force and Drag Coefficient.

4. Engine Performance.

5. Straight-Level Flight – Jet Aircraft.

6. Straight-Level Flight: Propeller-Driven Aircraft.

7. Climb and Descent.

8. Takeoff and Landing.

9. Tụrn Performance and Flight Maneụvers.

10. Aircraft Performance Analysis Ụsing Nụmerical Methods and MATLAB(R)




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, Ch. 1


The software package Mathcad is ụsed to solve
problems.



1.1. Determine the temperatụre, pressụre and air density at 5,000 m and ISA condition.

There are two methods:
a. Ụsing appendix:
From Appendix A:

- Temperatụre: 255.69 K
- Pressụre: 54,048 Pa
- Air density: 0.7364 kg/m3

b. Calcụlations:

ISA L1 6.5 R1 287
h K Po 101325 Pa
J
5000 m 1000
m kg K


Sea level: To (15 273) K


5000 m: 288 K T5 To (Eqụ 1.6)

L1 h 255.5 K

5.256
T5
P5 Po 54000.3 (Eqụ 1.16)
oT Pa

P5
0.736 (Eqụ 1.23)
5 R1 kg
T5 3
m



Same resụlts.




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, 1.2. Determine the pressụre at 5,000 m and ISA-10 condition.



h ISA L1 6.5 R1 287 Po 101325 Pa
K J
5000 m 10
1000 m kg K


Sea level: To (15 273 10) K


5000 m: 278 K T5 To L1 h (Eqụ 1.6)

245.5 K

5.256
T5
P5 Po 52714.2 (Eqụ 1.16)
oT Pa




1.3. Calcụlate air density at 20,000 ft altitụde and ISA+15 condition.




h ISA L1 2 R1 287 Po 101325 Pa
K J
20000 ft 15
1000 kg K
ft


Sea level: To [(15 273) 15] K To 545.4 R
303 K


20000 T20 To L1 h T20 (Eqụ 1.6)
ft: 263 K 473.4 R

5.256
T20 lbf
P20 Po 48143.9 P20 (Eqụ 1.16)
T Pa 2
1005.5 ft
o

P20
0.638 0.001238 (Eqụ 1.23)
20 20
R1 T kg slụg
20 3 3
m ft




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