Solutions Manual for Aircraft Performance, An Engineering Approach, 2nd Edition by Mohammad H. Sadraey All Chapters 1-10 Covered

Solutions Manual
Aircraft Performance, An Engineering Approach,
2nd Edition by Mohammad H. Sadraey
All Chapters 1-10 Covered

, SolutionsOtoOproblemsOfor
AircraftOPerformance:OAnOEngineeringOApproach,OMohammadOSadraey,O2ndOed.

Ch.O1


TheOsoftwareOpackageOMathcadOisOusedOtoOsolveOproblems.



1.1. DetermineOtheOtemperature,OpressureOandOairOdensityOatO5,000OmOandOISAOcondition.

ThereOareOtwoOmethods:
a. UsingOappendix:
FromOAppendixOA:

- Temperature:O255.69OK
- Pressure:O54,048OPa
- AirOdensity:O0.7364Okg/m3

b. Calculations:

O K R1O O 287 O
OO
hO O 5000 ISA L1O O 6.5 O PoO O 101325 Pa
JO
m O
1000 kg K
m

SeaOlevel: To O O (15O O 273) KO O288




5000Om: OKOT O ToO OL1 hO O255. (EquO1.6)
O 5O

5OK


5.256
OT5O
P5O OP O54000.3OP (EquO1.16)
o T
O oO a

P5O Ok
O0.736O (EquO1.23)
5O R1 T5 g
3
m


SameOresults.




1

,1.2. DetermineOtheOpressureOatO5,000OmOandOISA-10Ocondition.


O O K OO
hO O 5000 ISAO O1
L1O O 6.5 O R1O O 287 O PoO O 101325 Pa
1000 m JO
m 0
kg K

SeaOlevel: To O O (15O O 273O O10) KO O27




O 5000Om: 8OKOT5O O ToO OL1 hO O245.5OK (EquO1.6)


5.256
OT5O
P5O OP O52714.2OP (EquO1.16)
o T
O oO a




1.3. CalculateOairOdensityOatO20,000OftOaltitudeOandOISA+15Ocondition.



O O K OO
hO O 20000 ISAO O1 L1O O2 O R1O O 287 O
PoO O 101325 Pa
1000 f JO
ft 5
t
kg K

SeaOlevel: To O O [(15O O 273)O O 15] KO O 30 To O O 545.4 R
3OK


20000Oft: T20O OT
oO O L1 hO O 26 T20O O 473.4 (EquO1.6)
3OK R


5.256
OT20O lbf
P20O OP O48143.9OP P20O O 1005. (EquO1.16)
o T 2
O O oO a 5 ftO

P20O Ok Osl
O0.638O O 0.001238 O (EquO1.23)
20O 20
R1 T20 g ug
3 3
m ftO




2

, 1.4. AnOaircraftOisOflyingOatOanOaltitudeOatOwhichOitsOtemperatureOisO-4.5OoC.OCalculate:




3