Solution Manual for Aircraft Performance, 1st Edition by Mohammad H. Sadraey, 9781315366913, Covering Chapters 1-420 | Includes Rationales

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
R1T50.736kg
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
R1T200.638kg
m3 
200.001238slug
ft3 