Applied Fluid Mechanics (7th Edition)
7th Edition
ISBN: 9780132558921
Author: Robert L. Mott, Joseph A. Untener
Publisher: PEARSON
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Chapter 17, Problem 17.9PP
A highway sign is being designed to withstand winds of
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An aircraft is required to climb with 10° of climb angle. The aircraft has a mass of 30,000 kg and produces 50,000 N of drag. Assume zero angle of attack and zero thrust setting angle. How much thrust the aircraft engine must produce?
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Chapter 17 Solutions
Applied Fluid Mechanics (7th Edition)
Ch. 17 - A cylinder 25 mm in diameter is placed...Ch. 17 - As part of an advertising sign on the top of a...Ch. 17 - Determine the terminal velocity (see Section 2.6.4...Ch. 17 - Calculate the moment at the base of a flagpole...Ch. 17 - A pitcher throws a baseball without spin with a...Ch. 17 - A parachute in the form of a hemispherical cup 1.5...Ch. 17 - Calculate the required diameter of a parachute in...Ch. 17 - A ship tows an instrument in the form of a 30...Ch. 17 - A highway sign is being designed to withstand...Ch. 17 - Assuming that a semitrailer behaves as a square...
Ch. 17 - A type of level indicator incorporates four...Ch. 17 - Prob. 17.12PPCh. 17 - A bulk liquid transport truck incorporates a...Ch. 17 - A wing on a race car is supported by two...Ch. 17 - Prob. 17.15PPCh. 17 - The four designs shown in Fig. 17.16 for the cross...Ch. 17 - Prob. 17.17PPCh. 17 - Prob. 17.18PPCh. 17 - An antenna in the shape of a cylindrical rod...Ch. 17 - Prob. 17.20PPCh. 17 - Prob. 17.21PPCh. 17 - Prob. 17.22PPCh. 17 - Assume that curve 2 in Fig. 17.5 is a true...Ch. 17 - Prob. 17.24PPCh. 17 - Prob. 17.25PPCh. 17 - A small, fast boat has a specific resistance ratio...Ch. 17 - Prob. 17.27PPCh. 17 - Assume that Fig. 17.11 shows the performance of...Ch. 17 - Calculate the total drag on an airfoil that has a...Ch. 17 - Prob. 17.30PPCh. 17 - Prob. 17.31PPCh. 17 - Prob. 17.32PPCh. 17 - Prob. 17.33PP
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- Task 2:An airplane with a NACA 662-215 airfoil cruises at 170 m/s at an altitude of 4550 m. The airfoil has an aspect ratio of 9 with a span of 30 m. Determine the lift and drag forces then determine the power required to overcome drag. Consider the airplane flying at an angle of attack equal to 2.arrow_forward1. A piston-prop aircraft has a wing loading of 1600 N/m², wing area of 25 m² and its drag polar is given by Cp 1.5. The reciprocating engine develops 750 kW at sea level, and the propulsive efficiency of the engine-propeller combination is 0.85. Draw the power-available and power-required curves at sea level. Determine the maximum and minimum speeds for level flight at sea level. What is the minimum power required for level flight at sea level? Determine the corresponding velocity and lift coefficient. 0.025 + 0.05C. The maximum lift coefficient isarrow_forwardAs3. An airfoil is placed on the test section of a wind tunnel where the test section radius is 3 inches and inlet air velocity is 4 ft/s. a. Calculate the velocity around the airfoil if the diameter of the inlet is 9 inches. b.What is the pressure difference between the test section and the inlet c. If the pressure of the inlet is at 2116.6 psf, calculate the pressure at test section.arrow_forward
- Problem 04.010 - Calculate pressure on a wing Consider an airplane flying at a standard altitude of 5 km with a velocity of 256 m/s. At a point on the wing of the airplane, the velocity is 302 m/s. Calculate the pressure at this point. At 5 Km, ambient pressure is 5.4 × 104 N/m², temperature is 255.7 K, Cp is 1005 J/kg.K, and the density is 0.7361 kg/m³. The pressure is 104 N/m². Xarrow_forwardThe spoiler, shown in figure 1, will be fitted at the back end of a stock car to give it downforce on the track. The pressure distribution and average shear stress on the top surface are given and the data on the bottom surface can be neglected. The car can reach a maximum speed of 270 km/h on the track. The spoiler has a length and a widthof 1.2 m and 0.3 m, respectively. The density of the air is 1.2 kg/m2. Calculate the lift and drag coefficients of the spoiler.arrow_forwardThe spoiler, shown in figure 1, will be fitted at the back end of a stock car to give it downforce on the track. The pressure distribution and average shear stress on the top surface are given and the data on the bottom surface can be neglected. The car can reach a maximum speed of 270 km/h on the track. The spoiler has a length and a width of 1.2 m and 0.3 m, respectively. The density of the air is 1.2 kg/m?. Calculate the lift and drag coefficients of the spoiler. Tave = 500 N/m2 P= 1.5 kN/m? P= 0.15 kN/m² U Figure 1arrow_forward
- Calculate the power of the wind at a site that has wind speed of 12 m/s, air density of 1.2 kg/m3. The wind turbine at the site has a rotor diameter of 180 m. What is the maximum power that can be delivered by the wind turbine? (Assume π=3,14)arrow_forwardPlease help me with this convert 95 mph to m/s convert 488 x 10^-9 m to micrometersarrow_forwardQ1) A new computer drive is proposed to have a disc, as shown in Fig. 1. The dise is to rotate at 9,000 rpm, and the reader head is to be positioned 0.011 in. above the surface of the disc. Estimate the shearing force on the reader head as a result of the air between the disc and the head. Use v air = 1.47 x 10-5 m2/s. Stationary reader head 6 mm dia. 9,000 rpm 0.011 mm 55 mm Rotating disc Fig. (1).arrow_forward
- A B-2A is flying at 42,500 ft in standard day conditions at 420 KTAS. The mean chord length is 39.6ft.A) Find the overall or total Reynolds number for the aircraft.arrow_forwardQuestion 3 The wind resource at hub-height for a wind turbine with rated wind speed 11 m/s and cut- in wind speed 3.9 m/s is described by a Weibull distribution with a shape factor 1.7 and a scale factor 8.5 m/s. Give the number of hours per year during which the wind turbine is generating but below its rated power (Take a full year as 8760 hours)arrow_forwardProblem 06.002 - Calculate total drag An airplane weighing 5,000 lb is flying at standard sea level with a velocity of 525 mi/h. At this velocity, the L/D ratio is a maximum. The wing area and aspect ratio are 200 ft² and 8.5, respectively. The Oswald efficiency factor is 0.93. Calculate the total drag on the airplane. Assume poo = 0.002377 slug/ft³. The total drag on the airplane is lb.arrow_forward
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