Aircraft is in climbing flight. It has the following parameters: Aircraft mass m 237 tonnes Wing planform area S 280 m² Airspeed VTAS 168 m/s Total Thrust T 250 kN Air density ρ 1.0 kg/m³ Drag polar CD = 0.015+0.0576C The following assumption are considered: • Constant thrust • Small climb angle • Small angle of attack Calculate the climb angle.
Aircraft is in climbing flight. It has the following parameters: Aircraft mass m 237 tonnes Wing planform area S 280 m² Airspeed VTAS 168 m/s Total Thrust T 250 kN Air density ρ 1.0 kg/m³ Drag polar CD = 0.015+0.0576C The following assumption are considered: • Constant thrust • Small climb angle • Small angle of attack Calculate the climb angle.
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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Question

Transcribed Image Text:Aircraft is in climbing flight. It has the following parameters:
Aircraft mass
m
237 tonnes
Wing planform area
S
280 m²
Airspeed
VTAS
168 m/s
Total Thrust
T
250 kN
Air density
ρ
1.0 kg/m³
Drag polar
CD
=
0.015+0.0576C
The following assumption are considered:
• Constant thrust
• Small climb angle
• Small angle of attack
Calculate the climb angle.
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