01: An airplane weighing 180,000 N has a wing area of 45 m² and rate of climb of 2,000m/min at a speed of 540 km/h at 3 km altitude (p= 0.909 kg/m³), the drag polar given by Cp = 0.017+ 0.05 C². Answer the following by choosing the correct statement: 1. What do you mean by rate of climb? a) Vertical velocity of an aircraft b) Lift of an aircraft c) Thrust required d) Drag polar 2. The climb angle y: a) y = 12.5° b) y = 13° c) y = 13.5° d) y = 14° 3. The lift coefficient C1 at climb is: a) C1 = 0.14 b) C1 = 0.26 c) C1 = 0.38 d) C = 0.5 4. The thrust required Tr is: a) TR=51860 N b) Tr= 51160 N c) TR= 61860 N d) Tr = 61160 N 5. The power required Pr is: a) PR = 6574 kW b) PR= 7674 kW c) PR= 8774 kW d) PR = 9874 kW

01: An airplane weighing 180,000 N has a wing area of 45 m² and rate of climb of 2,000m/min at a speed of 540 km/h at 3 km altitude (p= 0.909 kg/m³), the drag polar given by Cp = 0.017+ 0.05 C². Answer the following by choosing the correct statement: 1. What do you mean by rate of climb? a) Vertical velocity of an aircraft b) Lift of an aircraft c) Thrust required d) Drag polar 2. The climb angle y: a) y = 12.5° b) y = 13° c) y = 13.5° d) y = 14° 3. The lift coefficient C1 at climb is: a) C1 = 0.14 b) C1 = 0.26 c) C1 = 0.38 d) C = 0.5 4. The thrust required Tr is: a) TR=51860 N b) Tr= 51160 N c) TR= 61860 N d) Tr = 61160 N 5. The power required Pr is: a) PR = 6574 kW b) PR= 7674 kW c) PR= 8774 kW d) PR = 9874 kW

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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Concept explainers

Pressure Vessels

The term pressure vessel refers to a closed container that contains gas or liquid at a different pressure than environment pressure. The pressure vessels have a wide scale of applications in our day-to-day lives and other industrial places. Some common examples of pressure vessels are gas cylinders, autoclaves, compressor vessels, etc.

Question

01: An airplane weighing 180,000 N has a wing area of 45 m² and rate of climb of
2,000m/min at a speed of 540 km/h at 3 km altitude (p= 0.909 kg/m³), the drag polar
given by Cp = 0.017+ 0.05 C².
Answer the following by choosing the correct statement:
1. What do you mean by rate of climb?
a) Vertical velocity of an aircraft
b) Lift of an aircraft
c) Thrust required
d) Drag polar
2. The climb angle y:
a) y = 12.5°
b) y = 13°
c) y = 13.5°
d) y = 14°
3. The lift coefficient C1 at climb is:
a) C1 = 0.14
b) C1 = 0.26
c) C1 = 0.38
d) C = 0.5
4. The thrust required Tr is:
a) TR=51860 N
b) Tr= 51160 N
c) TR= 61860 N
d) Tr = 61160 N
5. The power required Pr is:
a) PR = 6574 kW
b) PR= 7674 kW
c) PR= 8774 kW
d) PR = 9874 kW

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