no previous attempt please At high altitude air temperature is low and ice formation on wings can cause serious issues for air crafts.A solution to this problem is to install heating elements within the wings. An aircraft is cruising at aspeed of 120 m/s at an altitude around 12,000 ft where air temperature is -8°C and pressure is 65 kPa.For safety, the surface temperature of the wing is to be maintained at 8°C. The characteristic length ofthe wing is 2.1 m. The area of the wing is 2.1 m by 6 m. Previous measurements showed that the averagefriction coefficient between the wing and air at this condition is 0.002. You can assume the air flow to beturbulent throughout. Determine the average heat flux that the heater must be able to supply for safeflying conditions.w/ni1963.5 w

Given-Information:- Vair craft = 120 m/sTair = -8°CTwing = 8°CLc = 2.1 mcf = 0.002h = 12,000 ftp =…

Answered: ttempt please

Engineering

Mechanical Engineering

ttempt please

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 5.65P

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Question

no previous attempt please

At high altitude air temperature is low and ice formation on wings can cause serious issues for air crafts.
A solution to this problem is to install heating elements within the wings. An aircraft is cruising at a
speed of 120 m/s at an altitude around 12,000 ft where air temperature is -8°C and pressure is 65 kPa.
For safety, the surface temperature of the wing is to be maintained at 8°C. The characteristic length of
the wing is 2.1 m. The area of the wing is 2.1 m by 6 m. Previous measurements showed that the average
friction coefficient between the wing and air at this condition is 0.002. You can assume the air flow to be
turbulent throughout. Determine the average heat flux that the heater must be able to supply for safe
flying conditions.
w/ni
1963.5 w

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