Mohammad H. Sadraey
TEST BANK
Aircraft Performance
97813153669131st Edition 1 Contents Chapter 1. Atmosphere ................................ ................................ ................................ ................................ . 2 Chapter 2. Equations of Motion ................................ ................................ ................................ .................. 20 Chapter 3. Drag Force and Drag Coefficient ................................ ................................ ............................... 46 Chapter 4. Thrust Force ................................ ................................ ................................ .............................. 88 Chapter 5. Straight Level Flight – Jet Aircraft ................................ ................................ ........................... 115 Chapter 6. Straight Level Flight - Prop -Driven Aircraft ................................ ................................ ............. 174 Chapter 7. Climb and Descent ................................ ................................ ................................ .................. 221 Chapter 8. Take Off and Landing ................................ ................................ ................................ .............. 275 Chapter 9. Turn Perfo rmance and Flight Maneuvers ................................ ................................ ............... 332 Chapter 10. Aircraft Performance Simulation Using Numerical Methods ................................ ............... 386 End ................................ ................................ ................................ ................................ ............................ 420 Solutions Manual to accompany Aircraft Performance Analysis An Engineering Approach The software pack age Mathcad is used to solve majority of the problems . 2 Chapter 1 . Atmosphere 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: Same results. Sea level: 5000 m: (Equ 1.6) (Equ 1.16) (Equ 1.23) h 5000 m
ISA
L1 6.5K
1000 m
R1 287J
kgK
Po101325 Pa
To15 273( )K 288K
T5ToL1h 255.5 K
P5PoT5
To
5.256
54000.3 Pa
5P5
R1T50.736kg
m3 3 1.2. Determine the pressure at 5,000 m and ISA -10 condition. 1.3. Calculate air density at 20,000 ft altitude and ISA+15 condition. Sea level: 5000 m: (Equ 1.6) (Equ 1.16) Sea level: 20000 ft: (Equ 1.6) (Equ 1.16) (Equ 1.23) h 5000 m
ISA 10
L1 6.5K
1000 m
R1 287J
kgK
Po101325 Pa
To15 273 10 ( )K 278K
T5ToL1h 245.5 K
P5PoT5
To
5.256
52714.2 Pa
h20000 ft
ISA 15
L1 2K
1000 ft
R1 287J
kgK
Po101325 Pa
To15 273( )15 [ ]K 303K
To545.4 R
T20ToL1h 263K
T20473.4 R
P20PoT20
To
5.256
48143.9 Pa
P201005.5lbf
ft2
20P20
R1T200.638kg
m3
200.001238slug
ft3
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