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We want to predict the drag force on a remote-control airplane as it flies through air having a density of 1.21 kg/m³ and a viscosity of 1.76x 10-5 Pa-s. The airplane's fuselage has a diameter of 200 mm and the airplane will fly through air at a speed of 32 m/s. A model of the airplane's fuselage will be tested in a pressurized wind tunnel. The diameter of the model is 75 mm and the density and viscosity of the air in the wind tunnel are 3.00 kg/m³ and 1.82x 10- Pa-s, respectively. a) The diameter of the airplane's fuselage will be used to define the Reynolds number Re, for the flow around the fuselage. Compute the Reynolds number for the flow around the airplane's fuselage (answer: Re, = 4.40x 10³). b) Find the speed of the air that should be used to test a model of the fuselage in the wind tunnel to correctly model dynamic conditions (answer: 35.6 m/s). c) The model is tested in the wind tunnel at four speeds that bracket the speed computed above. The measured drag forces on the fuselage's model at these four speeds are (1) 1.62 N at 27.2 m/s, (2) 2.29 N at 32.4 m/s, and (3) 3.08 N at 37.5 m/s, and (4) 3.97 N at 42.7 m/s. The frontal area of the airplane's fuselage will be used to define the drag coefficient C, for the fuselage. Compute Re, and C, for the fuselage at each tested flow condition.

We want to predict the drag force on a remote-control airplane as it flies through air having a density of 1.21 kg/m³ and a viscosity of 1.76x 10-5 Pa-s. The airplane's fuselage has a diameter of 200 mm and the airplane will fly through air at a speed of 32 m/s. A model of the airplane's fuselage will be tested in a pressurized wind tunnel. The diameter of the model is 75 mm and the density and viscosity of the air in the wind tunnel are 3.00 kg/m³ and 1.82x 10- Pa-s, respectively. a) The diameter of the airplane's fuselage will be used to define the Reynolds number Re, for the flow around the fuselage. Compute the Reynolds number for the flow around the airplane's fuselage (answer: Re, = 4.40x 10³). b) Find the speed of the air that should be used to test a model of the fuselage in the wind tunnel to correctly model dynamic conditions (answer: 35.6 m/s). c) The model is tested in the wind tunnel at four speeds that bracket the speed computed above. The measured drag forces on the fuselage's model at these four speeds are (1) 1.62 N at 27.2 m/s, (2) 2.29 N at 32.4 m/s, and (3) 3.08 N at 37.5 m/s, and (4) 3.97 N at 42.7 m/s. The frontal area of the airplane's fuselage will be used to define the drag coefficient C, for the fuselage. Compute Re, and C, for the fuselage at each tested flow condition.

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
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We want to predict the drag force on a remote-control airplane as it flies through air having a density of 1.21 kg/m³ and a viscosity of 1.76x10- Pa-s. The airplane's fuselage has a diameter of 200 mm and the airplane will fly through air at a speed of 32 m/s. A model of the airplane's fuselage will be tested in a pressurized wind tunnel. The diameter of the model is 75 mm and the density and viscosity of the air in the wind tunnel are 3.00 kg/m³ and 1.82× 10-5 Pa-s, respectively. a) The diameter of the airplane's fuselage will be used to define the Reynolds number Re, for the flow around the fuselage. Compute the Reynolds number for the flow around the airplane's fuselage (answer: Re, = 4.40x 10'). b) Find the speed of the air that should be used to test a model of the fuselage in the wind tunnel to correctly model dynamic conditions (answer: 35.6 m/s). c) The model is tested in the wind tunnel at four speeds that bracket the speed computed above. The measured drag forces on the fuselage's model at these four speeds are (1) 1.62 N at 27.2 m/s, (2) 2.29 N at 32.4 m/s, and (3) 3.08 N at 37.5 m/s, and (4) 3.97 N at 42.7 m/s. The frontal area of the airplane's fuselage will be used to define the drag coefficient C, for the fuselage. Compute Re, and C, for D the fuselage at each tested flow condition. d) The Reynolds number range in part (c) spans the range where the remote-control airplane's fuselage will be operated. Use the results of (c) to predict a value for the fuselage's C, in the Reynolds number region where the remote-control airplane will be operated. e) Find the expected drag force on the 200-mm diameter remote-control airplane's fuselage as it flies through the 1.21 kg/m³ air at 32 m/s (answer: 6.42 N). D= 200 mm V= 32 m/s p= 1.21 kg/m³ µ = 1.76×10-5 Pa-s FDRAG = ?
Transcribed Image Text:We want to predict the drag force on a remote-control airplane as it flies through air having a density of 1.21 kg/m³ and a viscosity of 1.76x10- Pa-s. The airplane's fuselage has a diameter of 200 mm and the airplane will fly through air at a speed of 32 m/s. A model of the airplane's fuselage will be tested in a pressurized wind tunnel. The diameter of the model is 75 mm and the density and viscosity of the air in the wind tunnel are 3.00 kg/m³ and 1.82× 10-5 Pa-s, respectively. a) The diameter of the airplane's fuselage will be used to define the Reynolds number Re, for the flow around the fuselage. Compute the Reynolds number for the flow around the airplane's fuselage (answer: Re, = 4.40x 10'). b) Find the speed of the air that should be used to test a model of the fuselage in the wind tunnel to correctly model dynamic conditions (answer: 35.6 m/s). c) The model is tested in the wind tunnel at four speeds that bracket the speed computed above. The measured drag forces on the fuselage's model at these four speeds are (1) 1.62 N at 27.2 m/s, (2) 2.29 N at 32.4 m/s, and (3) 3.08 N at 37.5 m/s, and (4) 3.97 N at 42.7 m/s. The frontal area of the airplane's fuselage will be used to define the drag coefficient C, for the fuselage. Compute Re, and C, for D the fuselage at each tested flow condition. d) The Reynolds number range in part (c) spans the range where the remote-control airplane's fuselage will be operated. Use the results of (c) to predict a value for the fuselage's C, in the Reynolds number region where the remote-control airplane will be operated. e) Find the expected drag force on the 200-mm diameter remote-control airplane's fuselage as it flies through the 1.21 kg/m³ air at 32 m/s (answer: 6.42 N). D= 200 mm V= 32 m/s p= 1.21 kg/m³ µ = 1.76×10-5 Pa-s FDRAG = ?
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