Consider an airplane cruising at an altitude of 10 km where standard atmospheric conditions are –50°c and 26.5 kpa at a speed of 990 km/h. each wing of the airplane can be modeled as a 25-m × 3-m flat plate, and the friction coefficient of the wings is 0.0016. using the momentum-heat transfer analogy, determine the heat transfer coefficient for the wings at cruising conditions. the properties of air at –50°c and 1 atm are: cp =0.999 kj/kg·kpr = 0.7440

h = 110.84 w/m^2.K

Explanation:

Given data:

properties of air at - 50 degree celcius

Cp = 0.999 J/kg K

Pr = 0.744

from ideal gas equation we know that

PV = mRT

                  = 0.4141 kg/m^3

From modified reynold's analogue

h = 110.84 w/m^2.K

the equation above shows how temperature f, measured in degrees fahrenheit, relates to a temperature c, measured in degrees celsius. based on the equation, which of the following must be true?

a temperature increase of 1 degree fahrenheit is equivalent to a temperature increase of

5

9

degree celsius.

a temperature increase of 1 degree celsius is equivalent to a temperature increase of 1.8 degrees fahrenheit.

a temperature increase of

5

9

degree fahrenheit is equivalent to a temperature increase of 1 degree celsius.

a) i only

b) ii only

c) iii only

d) i and ii only