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Solution Manual for Aircraft Performance, 1st Edition by Mohammad H. Sadraey, 9781315366913, Covering Chapters 1-10 | Includes Rationales €25,83
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Solution Manual for Aircraft Performance, 1st Edition by Mohammad H. Sadraey, 9781315366913, Covering Chapters 1-10 | Includes Rationales
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Solution Manual for Aircraft Performance, 1st Edition by Mohammad H. Sadraey, 9781315366913, Covering Chapters 1-10 | Includes Rationales

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  • 10 juni 2024
  • 421
  • 2023/2024
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  • 9781315366913
  • sadraey solutions manual
  • engineering approach 1st
  • sadraey 1st edition
  • 9781315366913 sadraey
  • moha
  • aircraft performance manual
  • mohammad h sadraey 1st edition
  • 1st edition mohammad h sadraey

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Voorbeeld van de inhoud

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  4 1.4. An aircraft is flying at an altitude at which its temperature is -4.5 oC. Calculate: a. Altitude in ISA condition b. Altitude in ISA+10 condition c. Altitude in ISA -10 condition Sea level: (Equ 1.6) (Equ 1.6) (Equ 1.6) L1 6.5K
1000 m
To15°C
To288.15 K
ISA
Talt4.5 273 ( )K 
Talt268.5 K
TISATalt268.5 K
TISAToL1h
h1ToTISA
L13023 m 
ISA 10
T 10
TISA4.5T 273 ( )K 
TISA258.5 K
TISAToL1h
h2ToTISA
L14562 m 
ISA 10
T 10
TISA4.5T 273 ( )K 
TISA278.5 K
TISAToL1h
h3ToTISA
L11485 m  5 1.5. Determine r elative density ( ) at ISA -20 condition and 80,000 ft altitude. 1.6. Determine the temperature at 70,000 ft and ISA condition. Sea level: Second layer: (Equ 1.21) (Equ 1.23) (Equ 1.25) Sea level: Second layer: h80000 ft
ISA 20
R1 287J
kgK
Po101325 Pa
o0.00237slug
ft3
To15 273( )20 [ ]K 268K 
To482.4 R
To5.15 °C
T8056 273 20 ( )K 
T80354.6 R
T80197K
P80C0.2234 Poe36089 80000
20807 2.743 103 Pa  
80CP80C
R1T800.049kg
m3 
80C
o0.04
h70000 ft
ISA
To15 273( )K 288K 
To518.4 R
T7056 273 ( )K 
T70390.6 R
T70217K 6 1.7. An aircraft is flying at an altitude at which its temperature and pressure are 255 K and 4.72 × 104 Pa. Calculate: a. pressure altitude From Appendix A, for T = 255 K; h = 5,000 m b. temperature Altitude From Appendix A, for P = 4 .72 × 104 Pa; h = 6,000 m c. density altitude Interpolation: From Appendix A, for  = 0.645 kg/m3; h = 6,215 m (Equ 1.23) T1 255K
P1 4.72104 Pa 
R1 287J
kgK
P1
R1T10.645kg
m3 
given
h 6500
0.6601 0.59
7000 60000.645 0.59
7000 h
f ind h()6215.4 7 1.8. An aircraft is flying at an altitude at which its pressure altitude and density altitude are 4000 m and 4200 m. Calculate the temperature at this altitude. 1.9. If the lapse rate (L) is 3 oC per 1000 ft, what is the temperature at 15,000 ft altitude? Interpolation: (Equ 1.23) Sea level: (Equ 1.6) R1 287J
kgK
h1 4000 m
P1 61660 Pa
h2 4200 m
Given
10.7
0.7364 0.8193
5000 40000.73641
5000 4200
Find1()0.803
10.803kg
m3
P
RT
T1P1
1R1267.551 K
h15000 ft
ISA
L1 3K
1000 ft
To15 273.15( )K 288.15 K 
To518.67 R
T15ToL1h 243.15 K 
T15437.67 R 8 1.10. An aircraft is flying at 20,000 ft altitude with speed of 400 km/hr and ISA condition. Wh at is aircraft Mach number? 1.11. Calculate air density at sea level and ISA condition, when humidity is 100%. Sea level: (Equ 1.6) (Equ 1.35) Sea level: Table 1.2 (Equ 1.29) (Equ 1.30) (Equ 1. 23) h20000 ft
ISA
L1 2K
1000 ft
V1 400km
hr
V1 111.111m
s
 1.4
R1 287J
kgK
To15 273.15( )K 288.15 K 
To518.67 R
T20ToL1h 248.15 K 
T20446.67 R
aR1T20 315.764m
s 
M1V1
a0.352
R1 287J
kgK
 100%
Po101325 Pa
To15 273.15( )K 288.15 K 
Pg1.7051 kPa
Pv
Pg
PvPg 1.705 103 Pa 
PaPoPv 9.962 104 Pa  
Pa
R1To1.205kg
m3  9 1.12. Determine the speed of sound at sea level and a. ISA condition b. ISA+12 c. ISA-18 1.13. What is the dynamic pressure when an aircraft is cruising at the altitude of 8,000 m and Mach number of 0.6? Sea level: (Equ 1.34) (Equ 1.34) (Equ 1.34) (Equ 1.20) (Equ 1.36) ISA
 1.4
R1 287J
kgK
To15 273.15( )K 288.15 K 
To518.67 R
aR1To 340.263m
s 
T 12K
TbToT 300.15 K 
aR1Tb 347.275m
s 
T 18K
TcToT 270.15 K 
aR1Tc 329.464m
s 
Po101325 Pa
h 8000 m
M1 0.6
P8Po0.2234 e11000 mh
6342 m 36327.632 Pa  
q 0.7 P8 M12 9154.6 Pa 

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