100% tevredenheidsgarantie Direct beschikbaar na betaling Zowel online als in PDF Je zit nergens aan vast
logo-home
Eerder door jou gezocht
Eerder door jou gezocht
logo
Solution Manual for Aircraft Performance, 1st Edition by Mohammad H. Sadraey, 9781315366913, Covering Chapters 1-10 | Includes Rationales €25,66   In winkelwagen
Snel navigeren naar
Voorbeeld
  2.  
  3. Aircraft Performance, 1st Edition By Mohammad H. S
  4.  
  5. Aircraft Performance, 1st Edition by Mohammad H. S

Tentamen (uitwerkingen)

Solution Manual for Aircraft Performance, 1st Edition by Mohammad H. Sadraey, 9781315366913, Covering Chapters 1-10 | Includes Rationales
 9 keer bekeken  0 keer verkocht
  • Vak
  • Aircraft Performance, 1st Edition by Mohammad H. S
  • Instelling
  • Aircraft Performance, 1st Edition By Mohammad H. S
  • Boek
  • Aircraft Performance

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

Voorbeeld 10 van de 421  pagina's

Document informatie

  • 10 juni 2024
  • 421
  • 2023/2024
  • Tentamen (uitwerkingen)
  • Vragen en antwoorden

Onderwerpen

  • 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

Gekoppeld boek

book image

Titel boek:

Auteur(s):

  • Uitgave:
  • ISBN:
  • Druk:

Meer samenvattingen voor studieboek

  • Aircraft Performance An Engineering Approach 1st Edition By Mohammad H. Sadraey 9781498776554 ALL Chapters
  • Aircraft Performance An Engineering Approach 1st Edition By Mohammad H. Sadraey 9781498776554 ALL Chapters
  • Aircraft Performance An Engineering Approach 1st Edition By Mohammad H. Sadraey 9781498776554 ALL Chapters
Alles voor dit studieboek (6)

Geschreven voor

  • Aircraft Performance, 1st Edition by Mohammad H. S
  • Aircraft Performance, 1st Edition by Mohammad H. S

Verkoper

avatar-seller
Examsonline

Ontvangen beoordelingen

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 

Voordelen van het kopen van samenvattingen bij Stuvia op een rij:

Verzekerd van kwaliteit door reviews

Verzekerd van kwaliteit door reviews

Stuvia-klanten hebben meer dan 700.000 samenvattingen beoordeeld. Zo weet je zeker dat je de beste documenten koopt!

Snel en makkelijk kopen

Snel en makkelijk kopen

Je betaalt supersnel en eenmalig met iDeal, creditcard of Stuvia-tegoed voor de samenvatting. Zonder lidmaatschap.

Focus op de essentie

Focus op de essentie

Samenvattingen worden geschreven voor en door anderen. Daarom zijn de samenvattingen altijd betrouwbaar en actueel. Zo kom je snel tot de kern!

Veelgestelde vragen

Wat krijg ik als ik dit document koop?

Je krijgt een PDF, die direct beschikbaar is na je aankoop. Het gekochte document is altijd, overal en oneindig toegankelijk via je profiel.

Tevredenheidsgarantie: hoe werkt dat?

Onze tevredenheidsgarantie zorgt ervoor dat je altijd een studiedocument vindt dat goed bij je past. Je vult een formulier in en onze klantenservice regelt de rest.

Van wie koop ik deze samenvatting?

Stuvia is een marktplaats, je koop dit document dus niet van ons, maar van verkoper Examsonline. Stuvia faciliteert de betaling aan de verkoper.

Zit ik meteen vast aan een abonnement?

Nee, je koopt alleen deze samenvatting voor €25,66. Je zit daarna nergens aan vast.

Is Stuvia te vertrouwen?

4,6 sterren op Google & Trustpilot (+1000 reviews)

Afgelopen 30 dagen zijn er 73918 samenvattingen verkocht

Opgericht in 2010, al 14 jaar dé plek om samenvattingen te kopen

Start met verkopen
€25,66
  • (0)
  Kopen