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Solution Manual for Aircraft Performance, 1st Edition by Mohammad H. Sadraey, 9781315366913, Covering Chapters 1-10 | Includes Rationales$26.08
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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 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
TISA4.5T 273 ( )K
TISA258.5 K
TISAToL1h
h2ToTISA
L14562 m
ISA 10
T 10
TISA4.5T 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 Poe36089 80000
20807 2.743 103 Pa
80CP80C
R1T800.049kg
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
R1T10.645kg
m3
given
h 6500
0.6601 0.59
7000 60000.645 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 40000.73641
5000 4200
Find1()0.803
10.803kg
m3
P
RT
T1P1
1R1267.551 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
aR1T20 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
R1To1.205kg
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
aR1To 340.263m
s
T 12K
TbToT 300.15 K
aR1Tb 347.275m
s
T 18K
TcToT 270.15 K
aR1Tc 329.464m
s
Po101325 Pa
h 8000 m
M1 0.6
P8Po0.2234 e11000 mh
6342 m 36327.632 Pa
q 0.7 P8 M12 9154.6 Pa
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