A finite wing with an area and aspect ratio of 21.5 m² and 5, respectively. The wing has a NACA 65- 210 airfoil, a span efficiency factor of 0.9, and a profile drag coefficient of 0.004. If the wing is at a 6° angle of attack, calculate C, and Cp. Hint: finite wing lift slope per degree (a) is related to infinite wing lift slope per degree (ao) as follows: ao a = ao 1+57.3· TARE where AR is the aspect ratio and e is the span efficiency factor.

A finite wing with an area and aspect ratio of 21.5 m² and 5, respectively. The wing has a NACA 65- 210 airfoil, a span efficiency factor of 0.9, and a profile drag coefficient of 0.004. If the wing is at a 6° angle of attack, calculate C, and Cp. Hint: finite wing lift slope per degree (a) is related to infinite wing lift slope per degree (ao) as follows: ao a = ao 1+57.3· TARE where AR is the aspect ratio and e is the span efficiency factor.

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter5: Analysis Of Convection Heat Transfer

Section: Chapter Questions

Problem 5.49P

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