Applied Fluid Mechanics: Global Edition
7th Edition
ISBN: 9781292019611
Author: Robert Mott
Publisher: Pearson Higher Education
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Chapter 17, Problem 17.4PP
Calculate the moment at the base of a flagpole caused by a wind of
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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.
A tractor-trailer truck has a drag area CDA = 8 m2 bare and6.7 m2 with an aerodynamic deflector (Fig. 7.18b). Its rollingresistance is 50 N for each mile per hour of speed.Calculate the total horsepower required at sea level withand without the deflector, if the truck moves at (a) 55 mi/hand (b) 75 mi/h.
A horizontal air duct reduces in cross-sectional area from 0.070 m² to 0.020 m². Assuming no losses, what pressure change will occur when 6.67 N/s of air flows? (Use y = 31.4 N/m for pressure and temperature conditions involved.)
Chapter 17 Solutions
Applied Fluid Mechanics: Global 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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- The energy distribution in the boundary layer over the free of a spillway was observed to be : u/U=(y/6)^0.34 The free stream velocity U is 20m/s and boundary layer thickness 42mm at a certain section. calculate displacement thickness and energy thickness.arrow_forwardA smooth square cylinder is put in 15 °C flowing water. The flow direction is perpendicular to the long axis of the cylinder (parallel to the square section). The edge length of the square is s=2.0m. The long axis length is L=5.0m. The flow velocity is v=0.046 m/s. The density of water is ρ=1000kg/m3. T he dynamic viscosity is η=1.15×10-3kg/m·s. (2) Find the drag coefficient CD_________arrow_forward1. A ship weighing 7200 tons has a KG of 5.20 m, a KB of 3.12 m and a KM of 5.35 m. In the voyage, has used 300 tons of fuel with Kg 0.6 m. If the free surface effect is neglected and assuming KM remains constant, calculate the angle of inclination of the ship.arrow_forward
- 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_forwardA truck having projected area of 6.5 m² and travelling at 72 km/h has a total resistance of 1.6 kN. Out of this resistance, 30% is due to rolling, 20% due to surface friction and rest is due to drag. Calculate the coefficient of drag if specific weight of air is 12 N/m^3.arrow_forwardDetermine the velocity required for take off for an aircraft with the following characteristics.Aircraft mass: 7200 kgWingspan: 15 mWing shape: rectangularWing chord length: 1.8 mWing airfoil: NACA 4415Wing angle of attack: 7× 0.5 + 5 degreesHint: Check NACA charts for required parameters.arrow_forward
- A small, fast boat has a specific resistance ratio of 0.06 (see Table 17.2) and displaces 125 long tons. Compute the total ship resistance and the power required to overcome drag when it is moving at 50 ft/s in seawater at 77°F.arrow_forwardThe purpose of this problem is to give you a feel for the magnitude ofReynolds number appropriate to real airplanes in actual flight. a. Consider the DC-3 shown in (1.1). The wing root chord length(distance from the front to the back of the wing where the wing joinsthe fuselage) is 14.25 ft. Consider the DC-3 flying at 200 miles perhour at sea level. Calculate the Reynolds number for the flow over thewing root chord. (This is an important number, because as we will seelater, it governs the skin-friction drag over that portion of the wing.)b. Consider the F-22 shown in (1.5), and also gracing the cover ofthis book. The chord length where the wing joins the center body is21.5 ft. Consider the airplane making a high-speed pass at a velocityof 1320 ft/s at sea level (Mach 1.2). Calculate the Reynolds number atthe wing root.arrow_forwardIn one of the pilot plants, a 30 m diameter horizontal axis wind turbines (HAWT) are mounted with its hub at 50 m above a ground surface that is covered by shrubs and hedges. For the given pilot project, estimate the ratio of power in the wind per 1 m2 of rotor area at the highest point that a rotor blade tip reaches, to the lowest point that it falls to?arrow_forward
- A) What is an adverse pressure gradient, and where does it occur on an airfoil (Show that onan airfoil using a free hand sketch)?B) What causes the flow to separate from an airfoil?C) What are the two major consequences of flow separation?D) A B-2A aircraft is flying at H ft in standard day conditions at a velocity V kn. If the meanchord length is C ft.i- Find the overall or total Reynolds number for the aircraft.ii- Find the percentage of the wing chord where laminar flow is present, if Reynoldsnumber is 500,000.arrow_forwardCompute for the lift force acting on a wing with an area of 56 sq. ft., velocity of 75 ft/s at an altitude of 5000 ft. Cl of the wing is 0.75. Calculate the drag of a certain wing with an area of 20 sq. meters , velocity of 75 m/s at an altitude of 2000m . Cd of the wing is 0.05. Compute for the drag of a rectangular wing with a chord of 4.5 ft and a span of 16 ft. if the dynamic pressure 80 psi. Cd of the wing is 0.030.arrow_forwardA horizontal air duct in cross-sectional area from 0.75 ft 2 to 0.20 ft 2 . Assuming no losses, whatpressure change P A -P B will occur when 1.50lb/s of air flows? Use specific weight 0.200lb/ft 3 for thepressure and temperature conditions involved. Assuming elevation at A and B is at the same level. (PLEASE draw a diagram if you could, that would be so helpful than you so much)arrow_forward
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