Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 1, Problem 1.18P
The purpose of this problem is to give you a feel for the magnitude of Reynolds number appropriate to real airplanes in actual flight.
a. Consider the DC-3 shown in Figure 1.1. The wing root chord length (distancc from the front to the back of the wing where the wing joins the fuselage) is 14.25 ft. Consider the DC-3 flying at 200 miles per hour at sea level. Calculate the Reynolds number for the flow over the wing root chord. (This is an important number, because as we will see later, it governs the skin-friction drag over that portion of the wing.)
b. Consider the F-22 shown in Figure 1.5, and also gracing the cover of this book. The chord length where the wing joins the center body is 21.5 ft. Consider the airplane making a high-speed pass at a velocity of 1320 ft/s at sea level (Mach 1.2). Calculate the Reynolds number at the wing root.
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The 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.
A wind tunnel with a 7/1 inlet and test ratio. The test section is at standard sea-level conditions with a velocity of 125 ft/s, calculate the height change in the U-tube instrument connected to the test and inlet section, with a liquid density of 2.1 slugs/ft^3. The flow is incompressible.
An airfoil section is being tested in a wind tunnel. The freestream
properties are: velocity = 160 mps,
pressure = SSLC, density = SSLC.
Determine the velocity (mps) at a
point on the airfoil where the
pressure is 94,000 Pa.
SSLC- STANDARD SEA LEVEL CONDITIONS
Chapter 1 Solutions
Fundamentals of Aerodynamics
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Ch. 1 - A U-tube mercury manometer is used to measure the...Ch. 1 - The German Zeppeins of World War I were dirigibles...Ch. 1 - Consider a circular cylinder in a hypersonic flow,...Ch. 1 - Derive Archimedes principle using a body of...Ch. 1 - Consider a light, single-engine, propeller-driven...Ch. 1 - Consider a flat plate at zero angle of attack in a...Ch. 1 - Consider the Space Shuttle during its atmospheric...Ch. 1 - The purpose of this problem is to give you a feel...Ch. 1 - For the design of their gliders in 1900 and 1901,...Ch. 1 - Consider the existence of a forward-facing axial...
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