HEAT+MASS TRANSFER:FUND.+APPL.
6th Edition
ISBN: 9780073398198
Author: CENGEL
Publisher: RENT MCG
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- Use FoilSim to investigate how an aircraft wing produces lift and drag by changing the values of
different factors that affect lift and drag.
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.
Example 2
During a high Reynolds number experiment, the total drag
force acting on a spherical body of diameter D, 12 cm
subjected to airflow at 1 atm and 5 °C is measured to be
5.2 N. The pressure drag acting on the body is calculated by
integrating the
pressure sensors throughout the surface) to be 4.9 N.
Determine the friction drag coefficient of the sphere.
pressure
distribution (measured by the use of
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- 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 0.34arrow_forwardA thin sheet of fiberboard weighs 90 N and lies on a rooftop,as shown in Fig. . Assume ambient air at 20°Cand 1 atm. If the coefficient of solid friction between boardand roof is σ ≈ 0.12, what wind velocity will generateenough fluid friction to dislodge the board?arrow_forward2. Taking off on a dry cement runway, to minimize the impact of aerodynamics on the acceleration, which angle of attack a do you recommend to the pilot near the end of the acceleration phase (that is, where the pilot can indeed play with the stick and adust his angle of attack)? The friction coefficient is Op = 0.02, Cro = 0.02, AR = 4 and the wing loading W/S = 460 kg/m². A 0° В 1.15° C 1.7° D) 3.4° E) None, because there is no influence of a on acceleration.arrow_forward
- Qs. 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 aircraftarrow_forwardExample 15.18 A car with passengers has a mass of 1200 kg and a frontal area of 1.8 m². It is traveling up a gradient of 1 in 25 at a speed of 75 km/h. The a king resistance of the car is given by R, = (0.0.cce 0.00 r V) Mg and the air resistance coefficient is Ot8688. The engine develops 50 kW corresponding to an engine speed of 4500 rpm. The rear axle ratio is 5:1 and the transmission efficiency is 96%. If the wheel radius is 34f.mm, determine the 1. tractive ree i ivice 2. tractive effort available at the wheels and 3. acceleration while moving up the gradientarrow_forwardWhat is the effect of Reynolds number on drag coefficient , lift coefficient and L/D ratioarrow_forward
- An aeroplane has a stalling speed of 100 kt in a steadylevel flight. When the aeroplane is flying a level turn witha load factor of 1.5, the stalling speed is...arrow_forward2. Use scale analysis to find an expression for 8/L and Nu, for flow over a flat plate with a thin thermal boundary Layer. (8 >> ST)arrow_forwardA 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 wingarrow_forward
- Air flowing over a 1-m-long flat plate at a velocity of 7 m/s has a friction coefficient given as Cf= 0.664(Vx/v) is the location along the plate. 1-0.5 where x Given:/The properties of air at 20°C are u = 1.825 × 10 kg/m-s, V =1.516 × 105 m-/s, and p= 1.204 kg/m -5 Determine the wall shear stress at x 0.6 m of the plate. Evaluate the air properties at 20°C and 1 atm. (Round the final answer to five decimál places. You must provide an answer before moving on to the next part.) The wall shear stress is | Nim2.arrow_forwardCalculate lift, drag and (T/W ratio) for an aeroplane with velocity 500 m/s, wing area 45 m2 , a drag coefficient 0.05 and a lift coefficient 0.9arrow_forwardConsider that you are in an area of Seattle where the wind is blowing at 40 km/h with a temperature of 0 ° C. If you can be mathematically modeled as a cylinder with diameter external of 0.3m and height of 1.70 m. Calculate the number of hot dogs that you need to eat to make up for the amount of energy you lose in heat form for an hour. Note 1: Consider that the external temperature of the clothes is kept constant at 25 ° C. Note 2: Consider a 150 kcal hot dog.arrow_forward
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