The rectangular wings of a microlight aircraft have a combined spanwise length of9.144 m and streamwise (direction of air flow) width of 0.9144 m The wings have acoefficient of form drag of 0.01 and a lift coefficient of 0.3 in cruise.When cruising at a speed of 150km/h and altitude of 3,000 feet, the temperature andabsolute pressure of the atmospheric air are 5ºC and 90 kPa, respectively.a) Calculate the density of the air at cruising altitude.b) Calculate the form drag on the wings.c) Calculate the Reynolds number of the wings.d) Calculate the skin friction drag on the wings.e) If the fuselage of the microlight is spherical with a diameter of 1m and the totaldrag of the aircraft is represented by the contributiocombined, and assuming the skin friction drag is negligible for the fuselage only,calculate the combined total drag force.fuselage and wingsf) Calculate the power required to overcome total drag in cruise, using the valuecalculated in part e).g) Calculate the maximum weight limit for the aircraft to be able to fly at this altitude.

Given Length = 9.144 m Width = 0.9144 m Drag coefficient = 0.01 Lift coefficient = 0.3 Altitude =…

The rectangular wings of a microlight aircraft have a combined spanwise length of 9.144 m and streamwise (direction of air flow) width of 0.9144 m The wings have a coefficient of form drag of 0.01 and a lift coefficient of 0.3 in cruise. When cruising at a speed of 150km/h and altitude of 3,000 feet, the temperature and absolute pressure of the atmospheric air are 5°C and 90 kPa, respectively. a) Calculate the density of the air at cruising altitude. b) Calculate the form drag on the wings. c) Calculate the Reynolds number of the wings.

The rectangular wings of a microlight aircraft have a combined spanwise length of 9.144 m and streamwise (direction of air flow) width of 0.9144 m The wings have a coefficient of form drag of 0.01 and a lift coefficient of 0.3 in cruise. When cruising at a speed of 150km/h and altitude of 3,000 feet, the temperature and absolute pressure of the atmospheric air are 5°C and 90 kPa, respectively. a) Calculate the density of the air at cruising altitude. b) Calculate the form drag on the wings. c) Calculate the Reynolds number of the wings.

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 5.24P: Engine oil at 100C flows over and parallel to a flat surface at a velocity of 3 m/s. Calculate the...

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The rectangular wings of a microlight aircraft have a combined spanwise length of 9.144 m and streamwise (direction of air flow) width of 0.9144 m The wings have a coefficient of form drag of 0.01 and a lift coefficient of 0.3 in cruise. When cruising at a speed of 150km/h and altitude of 3,000 feet, the temperature and absolute pressure of the atmospheric air are 5°C and 90 kPa, respectively. a) Calculate the density of the air at cruising altitude. b) Calculate the form drag on the wings. c) Calculate the Reynolds number of the wings. d) Calculate the skin friction drag on the wings. e) If the fuselage of the microlight is spherical with a diameter of 1m and the total drag of the aircraft is represented by the contribution of fuselage and wings combined, and assuming the skin friction drag is negligible for the fuselage only, calculate the combined total drag force. f) Calculate the power required to overcome total drag in cruise, using the value calculated in part e). g) Calculate…
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