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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