Solutions for Aircraft Performance, An Engineering Approach, 2nd Edition Sadraey (All Chapters included)
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Course
Aircraft Leadership
Institution
Aircraft Leadership
Complete Solutions Manual for Aircraft Performance, An Engineering Approach, 2nd Edition by Mohammad H. Sadraey ; ISBN13: 9781032245157. (Full Chapters included Chapter 1 to 10)....
1. Atmosphere. 2. Equations of Motion. 3. Drag Force and Drag Coefficient. 4. Engine Performance. 5. Straight-Level ...
Aircraft Performance,
An Engineering Approach
2nd Edition
by Mohammad H. Sadraey
Complete Chapter Solutions Manual
are included (Ch 1 to 10)
** Immediate Download
** Swift Response
** All Chapters included
, Solutions to problems for
Aircraft Performance: An Engineering Approach, Mohammad Sadraey, 2nd ed.
Ch. 1
The software package Mathcad is used to solve problems.
1.1. Determine the temperature, pressure and air density at 5,000 m and ISA condition.
There are two methods:
a. Using appendix:
From Appendix A:
- Temperature: 255.69 K
- Pressure: 54,048 Pa
- Air density: 0.7364 kg/m3
b. Calculations:
K J
h := 5000⋅ m ISA L1 := 6.5⋅ R1 := 287⋅ Po := 101325⋅ Pa
1000⋅ m kg ⋅ K
Sea level: To := ( 15 + 273) ⋅ K = 288 K
5000 m: T5 := To − L1⋅ h = 255.5 K (Equ 1.6)
5.256
T5
P5 := Po ⋅ = 54000.3 Pa (Equ 1.16)
To
P5 kg
ρ5 := = 0.736 (Equ 1.23)
R1⋅ T5 3
m
Same results.
1
, 1.2. Determine the pressure at 5,000 m and ISA-10 condition.
K J
h := 5000⋅ m ISA − 10 L1 := 6.5⋅ R1 := 287⋅ Po := 101325⋅ Pa
1000⋅ m kg ⋅ K
Sea level: To := ( 15 + 273 − 10) ⋅ K = 278 K
5000 m: T5 := To − L1⋅ h = 245.5 K (Equ 1.6)
5.256
T5
P5 := Po ⋅ = 52714.2 Pa (Equ 1.16)
To
1.3. Calculate air density at 20,000 ft altitude and ISA+15 condition.
K J
h := 20000⋅ ft ISA + 15 L1 := 2⋅ R1 := 287⋅ Po := 101325⋅ Pa
1000⋅ ft kg ⋅ K
Sea level: To := [ ( 15 + 273) + 15] ⋅ K = 303 K To = 545.4⋅ R
20000 ft: T20 := To − L1⋅ h = 263 K T20 = 473.4⋅ R (Equ 1.6)
5.256
T20 lbf
P20 := Po ⋅ = 48143.9 Pa P20 = 1005.5⋅ (Equ 1.16)
To ft
2
P20 kg slug
ρ20 := = 0.638 ρ20 = 0.001238⋅ (Equ 1.23)
R1⋅ T20 3 3
m ft
1.4. An aircraft is flying at an altitude at which its temperature is -4.5 oC. Calculate:
2
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