During flow over a given slender body such as a wing, the lift force, the upstream velocity, and the fluid density are measured. Explain how you would determine the lift coefficient. What area would you use in the calculations?
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Q: Calculate lift, drag and (T/W) for an aeroplane with velocity 500 m/s, wing area 45 m2 , a drag…
A: Given, V = 500 m/s A = 45 m2 CD = 0.05 CL = 0.9
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Q: Explain
A: given: explain lift force and lift coefficient
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A: Given question? What is induced drag on wing? Can it be minimized by wing shape?
During flow over a given slender body such as a wing, the lift force, the upstream velocity, and the fluid density are measured. Explain how you would determine the lift coefficient. What area would you use in the calculations?
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- A group of researchers from UMP conducted a project collaboration with an aircraft company to develop a small aircraft. The aircraft is designed to carry up to 2800 kg of total mass. The wing area of the aircraft is 30 m2. During takeoff, the lift coefficient of the aircraft is 0.45. Meanwhile during cruising, the drag coefficient of the aircraft is 0.035. iii. Evaluate the required power to maintain at cruising speed of 300 km/h.In a lifting flow over circular cylinder with vortex strength = 4m2/s, diameter = 0.2 m and density = 1.25 kg/m3. Determine the freestream velocity that generates lift coefficient = 0.45. Also, determine the lift and the drag forces per unit span.A cloud of coal particles is traveling through a system. The cloud diameter estimated to be 0.027 m and the individual particles are 50 um in diameter with the density of 1300 kg/m'. The total cloud is moving such that its drag coefficient is constant at 0.44. The individual particles in the cloud move much slower, such that the drag coefficient given by stock's law. The system has atmospheric air transporting and the cloud density is 190 kg/m3. Determine the ratio of internal velocity to cloud velocity. Atmospheric air density 1.2 kg/m'.
- An aircraft with symmetric airfoil of wing area 20 m2, flyingwith velocity 60km/hr experiences lift coefficient of 0.8. Considering the aircraft flying at sea level conditions, determine the mass of the aircraft.A group of researchers from UMP conducted a project collaboration with an aircraft company to develop a small aircraft. The aircraft is designed to carry up to 2800 kg of total mass. The wing area of the aircraft is 30 m2. During takeoff, the lift coefficient of the aircraft is 0.45. Meanwhile during cruising, the drag coefficient of the aircraft is 0.035. ii. Determine the load of the wingExample 3 The drag coefficient of a car increases when the sunroof is open, and it requires more aerodynamic drag. The car has a frontal area of 1.7 m2; and the C, values when the sunroof is closed and open are 0.32 and 0.41, respectively. If the car is moving at a constant velocity of 55 km/hr, determine the additional power consumption of the car when the sunroof is opened . Take the density of air to be 1.2 kg/m³. (a) if the air is calm, (b) if wind is blowing against the direction of the motion of the car at 30 km/hr, and (c) if wind is blowing in the same direction of motion of power to overcome the car at 50 km/hr.
- Use FoilSim to investigate how an aircraft wing produces lift and drag by changing the values of different factors that affect lift and dragQs. An aircraft is flying in level flight at a speed of 200 km/h through air (density, p = 1.2 kg/m³, and viscosity, μ = 1.6 x 10-5 N-s/m²). The lift coefficient at this speed is 0.4 and the drag coefficient is 0.0065. The mass of the aircraft is 800 kg. The effective lift area of the aircraftThe wing loading on an airplane is defined as the aircraft weight divided by the wing area. An airplane is cruising with a wing loading of 2500 Pa. The lift coefficient and drag coefficient are 0.30 and 0.06, respectively. Calculate the drag force if the wing planform area is 12 m2. Assume that the air density is unknown and not given.
- A 0.80-m-diameter, 1.2-m-high garbage can is found in the morning tipped over due to high winds during the night. Assuming the average density of the garbage inside to be 150 kg/m3 and taking the air density to be 1.25 kg/m3, estimate the wind velocity during the night when the can was tipped over. Take the drag coefficient of the can to be 0.7.The drag coefficient for a car with a frontal area of 26 ft? is being measured in an 8 ft x 8 ft wind tunnel. The density of air under the test conditions is 2.4 x 10 3 slugs/ft, When the air flow rate is, 500,000 ft/min, the drag force on the car was measured to be 170 lb. The drag coefficient under the test conditions is most nearly O 0.30 O 0.32 O 0.28 O 0.34Calculate the frontal area of a parachute of hemi-spherical shape which will allow aparachutejumper of weight 90 kg to descend with a steady velocity of 8 m/s ignoring air movement.The drag coefficient of parachute as determined from experiments is 1.5. Take the densityof air as 1.2 kg/m3