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5.13 A plane is traveling at 725 m/s at an altitude of 4000 m (where the air density is 0.819 kg/m³). If the air above the wing travels at 805 m/s and the air below the wing travels at 711 m/s and the wing has an area of 45.0 m², what lift force pushes up on the plane?

5.13 A plane is traveling at 725 m/s at an altitude of 4000 m (where the air density is 0.819 kg/m³). If the air above the wing travels at 805 m/s and the air below the wing travels at 711 m/s and the wing has an area of 45.0 m², what lift force pushes up on the plane?

College Physics
College Physics
11th Edition
ISBN:9781305952300
Author:Raymond A. Serway, Chris Vuille
Publisher:Raymond A. Serway, Chris Vuille
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is griven by in testing, it is the plane! CL = 2 s. What is the hrust? r at a velocity a total thrust h propeller? is given by CL = 2=0 + at a velocity otal thrust of propeller? Ta's call this kind of wing a Type III Wing. See the Hint in Problem 5.9. ..5.12 Create a plot of CL vs. (A,)/v for a Type I Wing, a Type II Wing, and Type III Wing (as defined in Problems 5.9 through 5.11) for 0 < (A»)/v < 2. ag force and In other words, your independent variable is the ratio (A»)/v.) (a) Which Wing Type produces the greatest amount of lift for a given value of (A,)/v? (b) Which Wing Type offers the "steadiest" control of CL as (A)/v is varied (i.e., which say, confirm Wing Type exhibits linear behavior)? (c) Explain why, physically, the Type II Wing exhibits a maximum value of CL at (A,)/v= 1. (d) Explain why, physically, r at a rate of taxies down the Type II Wing exhibits a value of CL = 0 at (A»)/v = 2. avels at 800 wing's lift syhat is the density is 0.819 kg/m³). If the air above the wing travels at 805 m/s and the air 5.13 A plane is traveling at 725 m/s at an altitude of 4000 m (where the air below the wing travels at 711 m/s and the wing has an area of 45.0 m², what lift force pushes up on the plane? e air above 5.14 A plane is traveling at 328 ft/s at an altitude of 10000 ft (where the air density is 0.001756 slug/ft³). If the lift coefficient is given by C, = a 0.230 for angle of attack a < 30°, and the wing has an area of 310.0 ft², what lift force pushes up on the plane when the angle of attack is 0°? 10°? 20°? he wing? a/(25.0°) + ne travels I the wind ent of this 5.15 A plane is traveling at 300 ft/s at an altitude of 8000 ft (where the air density is 0.001869 slug/ft³). If the plane ascends to an altitude of 11000 ft (where the air density is 0.001701 slug/ft°) and needs to maintain the same lift force. at what speed can it travel at the higher altitude? to recall 5.16 A plane is traveling at 350 ft/s at an altitude of 8000 ft (where the air density is tain the o /ft3). If the plane needs to slow to 280 ft/s and main- must it descend? First, calculate the (5.40) to wh (5.41) 0 kels
Transcribed Image Text:is griven by in testing, it is the plane! CL = 2 s. What is the hrust? r at a velocity a total thrust h propeller? is given by CL = 2=0 + at a velocity otal thrust of propeller? Ta's call this kind of wing a Type III Wing. See the Hint in Problem 5.9. ..5.12 Create a plot of CL vs. (A,)/v for a Type I Wing, a Type II Wing, and Type III Wing (as defined in Problems 5.9 through 5.11) for 0 < (A»)/v < 2. ag force and In other words, your independent variable is the ratio (A»)/v.) (a) Which Wing Type produces the greatest amount of lift for a given value of (A,)/v? (b) Which Wing Type offers the "steadiest" control of CL as (A)/v is varied (i.e., which say, confirm Wing Type exhibits linear behavior)? (c) Explain why, physically, the Type II Wing exhibits a maximum value of CL at (A,)/v= 1. (d) Explain why, physically, r at a rate of taxies down the Type II Wing exhibits a value of CL = 0 at (A»)/v = 2. avels at 800 wing's lift syhat is the density is 0.819 kg/m³). If the air above the wing travels at 805 m/s and the air 5.13 A plane is traveling at 725 m/s at an altitude of 4000 m (where the air below the wing travels at 711 m/s and the wing has an area of 45.0 m², what lift force pushes up on the plane? e air above 5.14 A plane is traveling at 328 ft/s at an altitude of 10000 ft (where the air density is 0.001756 slug/ft³). If the lift coefficient is given by C, = a 0.230 for angle of attack a < 30°, and the wing has an area of 310.0 ft², what lift force pushes up on the plane when the angle of attack is 0°? 10°? 20°? he wing? a/(25.0°) + ne travels I the wind ent of this 5.15 A plane is traveling at 300 ft/s at an altitude of 8000 ft (where the air density is 0.001869 slug/ft³). If the plane ascends to an altitude of 11000 ft (where the air density is 0.001701 slug/ft°) and needs to maintain the same lift force. at what speed can it travel at the higher altitude? to recall 5.16 A plane is traveling at 350 ft/s at an altitude of 8000 ft (where the air density is tain the o /ft3). If the plane needs to slow to 280 ft/s and main- must it descend? First, calculate the (5.40) to wh (5.41) 0 kels
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