(b) Recognise the difference between the skin friction drag and pressure drag. Explain which of these two drag forces is more significant for slender bodies such as aerofoils.
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- Based strictly on your understanding of the flat-plate theoryplus adverse and favorable pressure gradients, explainthe direction (left or right) for which airflow past theslender airfoil shape in Fig will have lower total(friction 1 pressure) drag.Consider a 1200 kg car presenting a front-end area 2.60 m2 and having a drag coefficient 0.385. It can achieve instantaneous acceleration 3.00 m/s2 when its speed is 10.0 m/s. Ignore any force of rolling resistance. Assume that the only horizontal forces on the car are static friction forward exerted by the road on the drive wheels and resistance exerted by the surrounding air, with density 1.20 kg/m3. (a) Find the friction force exerted by the road.(b) Suppose the car body could be redesigned to have a drag coefficient of 0.165 If nothing else changes, what will be the car's acceleration?(c)Assume that the force exerted by the road remains constant. Then what maximum speed could the car attain with D = 0.385?(d) What maximum speed could the car attain with D = 0.165?Problem 2: Consider laminar boundary layer flow past the square -plate arrangements in the figure below. Compared to the friction drag on a single square, how much larger is the drag of the four plates together as in configurations (a) and (b)? ↑ 1 (a) 1 2 3 4 1 2 (b) 3 4
- In the vertical wind tunnel used in paratrooper training, find the wind tunnel free speed required to keep a 75 kg person suspended in the air in a horizontal position. The height of this person is 1.7m and the width is 38cm and the front drag coefficient is around 1. Atmospheric pressure and temperature inside the tunnel are Patm = 85kPa and T = 25C, respectively.A wing of 2 percent camber, 5-in chord, and 30-in span istested at a certain angle of attack in a wind tunnel with sealevelstandard air at 200 ft/s and is found to have lift of 30 lbfand drag of 1.5 lbf. Estimate from wing theory (a) the angle ofattack, (b) the minimum drag of the wing and the angle of attackat which it occurs, and (c) the maximum lift-to-drag ratio.Air at 20°C and 1 atm flows at 3 m/s past a sharp flat plate2 m wide and 1 m long. (a) What is the wall shear stress atthe end of the plate? (b) What is the air velocity at a point4.5 mm normal to the end of the plate? (c) What is the totalfriction drag on the plate?
- Is it possible to mix multiple airfoil profiles for an aircraft wing? If so, then why.Consider an infinite wing with an NACA 1412 airfoil section and a chord length of 1 m. The wing is at an angle of attack 5° in an airflow velocity of 44 m/s at standard sea-level conditions. Calculate the lift, drag, and moment about the quarter chord per unit span.Air at 20°C and 1 atm fl ows at 50 ft/s past a thin fl at platewhose area (bL) is 24 ft2. If the total friction drag is 0.3 lbf,what are the length and width of the plate?
- Consider the equation v (t) = " (1 – e-le/m)t) For the free-falling bungee jumper with linear drag, assume a first jumper is 73.5 kg and has a drag coefficient of 12.5 kg/s. If a second jumper has a drag coefficient of 14.5 kg/s and a mass of 85 kg, how long will it take him to reach the same velocity jumper 1 reached in 8 s? (Round the final answer to three decimal places.)Name some applications in which a large drag is desired.Consider a 102 mph airflow over a flat plate with a span of 9.7 ft and a planform area of 60 ft2. The boundary layer transitioned from laminar to turbulent. If the total skin friction drag for the laminar section is 0.858 lbs, determine the location of the transition point. Assume SSLC, Provide answer in feet and round off answer to the nearest thousandths.