5 km. The wing has a NACA 65-210 A small aircraft is flying at steady level flight at an altitude airfoil with a plain flap, an area = 15 m², a span=10 m, and a span efficiency factor = 0.9. The weight of the aircraft is 3x104 N. Finite wing lift slope per degree (a) is related to infinite wing lift slope per degree (ao) as follows: a = ao where AR is the aspect ratio and e is the span efficiency 1+57.3– 20 T AR e factor. The pilot noticed that the air speed indicator is showing 40 m/s as the flight speed. The pilot suspects that this speed is not correct. Using calculation, verify pilot’s claim.
5 km. The wing has a NACA 65-210 A small aircraft is flying at steady level flight at an altitude airfoil with a plain flap, an area = 15 m², a span=10 m, and a span efficiency factor = 0.9. The weight of the aircraft is 3x104 N. Finite wing lift slope per degree (a) is related to infinite wing lift slope per degree (ao) as follows: a = ao where AR is the aspect ratio and e is the span efficiency 1+57.3– 20 T AR e factor. The pilot noticed that the air speed indicator is showing 40 m/s as the flight speed. The pilot suspects that this speed is not correct. Using calculation, verify pilot’s claim.
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
![A small aircraft is flying at steady level flight at an altitude
airfoil with a plain flap, an area =
of the aircraft is 3×10ª N. Finite wing lift slope per degree (a) is related to infinite wing lift slope
per degree (ao) as follows: a =
5 km. The wing has a NACA 65-210
15 m², a span = 10 m, and a span efficiency factor =0.9. The weight
ao
where AR is the aspect ratio and e is the
span
efficiency
ao
1+57.3-
TT. AR e
factor. The pilot noticed that the air speed indicator is showing 40 m/s as the flight speed. The pilot
suspects that this speed is not correct. Using calculation, verify pilot’'s claim.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F4f6c4b18-7c26-463c-8302-3011939a3ce9%2F6c0a5d97-5782-4fe4-9f91-a668880c2068%2F7pn8xe8_processed.png&w=3840&q=75)
Transcribed Image Text:A small aircraft is flying at steady level flight at an altitude
airfoil with a plain flap, an area =
of the aircraft is 3×10ª N. Finite wing lift slope per degree (a) is related to infinite wing lift slope
per degree (ao) as follows: a =
5 km. The wing has a NACA 65-210
15 m², a span = 10 m, and a span efficiency factor =0.9. The weight
ao
where AR is the aspect ratio and e is the
span
efficiency
ao
1+57.3-
TT. AR e
factor. The pilot noticed that the air speed indicator is showing 40 m/s as the flight speed. The pilot
suspects that this speed is not correct. Using calculation, verify pilot’'s claim.
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