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.

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

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Fluid Dynamics

The study of the flow of gases and liquids, usually in and around solid surfaces, is known as fluid dynamics in physics and engineering. Fluid dynamics, for example, can be used to evaluate the movement of air through an airplane wing or the surface of a vehicle. It can also be used in ship design to increase the speed at which ships pass through water.

Question

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 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 total
drag of the aircraft is represented by the contributio
combined, and assuming the skin friction drag is negligible for the fuselage only,
calculate the combined total drag force.
fuselage and wings
f) Calculate the power required to overcome total drag in cruise, using the value
calculated in part e).
g) Calculate the maximum weight limit for the aircraft to be able to fly at this altitude.

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