HEAT+MASS TRANSFER:FUND.+APPL.
6th Edition
ISBN: 9780073398198
Author: CENGEL
Publisher: RENT MCG
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Chapter 7, Problem 5CP
Define the frontal area of a body subjected to external flow. When is it appropriate to use the frontal area in drag and lift calculations?
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Define the frontal area of a body subjected to external flow. When is it appropriate to use the frontal area in drag and lift calculations?
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.
, A small aircraft has a wing area of 40 m2a lift coefficient of 0.45 at takeoff settings, and a total mass of 4000 kg. Determine (a) the takeoff speed of this aircraft at sea level at standard atmospheric conditions, (b) the wing loading, and (c) the required power to maintain a constant cruising speed of 360 km/h for a cruising drag coefficient of 0.035.
Chapter 7 Solutions
HEAT+MASS TRANSFER:FUND.+APPL.
Ch. 7 - What is the difference between the upstream...Ch. 7 - What is drag? What causes it? Why do we usually...Ch. 7 - Define the frontal area of a body subjected to...Ch. 7 - Air at 25C and 1 atm is flowing over a long flat...Ch. 7 - Air at 15C and 1 atm flows over a 0.3-m-wide plate...Ch. 7 - Water at 43.3C flows over a large plate at a...Ch. 7 - Prob. 57PCh. 7 - Prob. 97PCh. 7 - Prob. 102P
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- b) What is induced drag on wings? Can the induced drag be minimized by (1) long and narrow wings or (2) short and wide wings? Please justify your answer.arrow_forwardЕxample 5 The total mass, wing area, cruising speed, and air resistance power of a small aircraft are 1800 kg, 42 m², 280 km/hr, and 190 kW, respectively. Determine the lift and drag coefficients of this airplane while cruising at an altitude of 4000 m.arrow_forwardAn airplane is cruising at a velocity of 950 km/h in air whose density is 0.526 kg/m3. The airplane has a wing planform area of 90 m2. The lift and drag coefficients on cruising conditions are estimated to be 2.0 and 0.06, respectively. The power that needs to be supplied to provide enough trust to overcome wing drag is (a) 21,500 kW (b) 19,300 kW (c) 23,600 kW (d ) 25,200 kW (e) 26,100 kWarrow_forward
- (b) A 70 kg bicyclist is riding her 15 kg bicycle downhill on a road with a slope of 8° without pedaling or braking. The bicyclist has a frontal area of 0.45 m² and a drag coefficient of 1.1 in the upright position, and a frontal area of 0.4 m² and a drag coefficient of 0.9 in a racing position. If the downhill speed of the bicyclist (terminal velocity) can be determined when the total force acting on the "body" in the direction of movement is equal to zero, determine the percentage of down speed that she can be increased when she is in a racing position. Air temperature is 15°C and disregarding the rolling resistance and friction at the bearing.arrow_forwardWhat is flow separation? What causes it? What is the effect of flow separation on the drag coefficient?arrow_forwardThe form drag coefficient of a certain light aircraft is equal to 0.02. Its skin friction drag coefficient is 0.009. Determine its maximum lift-to-drag ratio (nearest hundredths) if its interference drag is 8 percent of its profile drag. The aircraft has an elliptical wing with an aspect ratio of 6.9.arrow_forward
- A person is driving his motorcycle at a speed of 90 km/h in air at 20°C. The frontal area of the motorcycle and driver is 0.75 m2. If the drag coefficient under these conditions is estimated to be 0.90, the drag force acting on the car in the flow direction is (a) 379 N (b) 204 N (c) 254 N (d ) 328 N (e) 420 Narrow_forwardThe 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.arrow_forwardDuring a winter day, wind at 58 km/h, 5°C, and 1 atm is blowing parallel to a 3.5-m-high and 9-m-long wall of a house. Approximating the wall surfaces as smooth, determine the friction drag acting on the wall. What would your answer be if the wind velocity has doubled? How realistic is it to treat the flow over side wall surfaces as flow over a flat plate?arrow_forward
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