Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 1, Problem 1.10P
Consider a Lear jet flying at a velocity of 250 m/s at an altitude of 10 km. where the density and temperature are
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Consider a Lear jet flying at a velocity of 250 m/s at an altitude of 10 km,where the density and temperature are 0.414 kg/m3 and 223 K,respectively. Consider also a one-fifth scale model of the Lear jet beingtested in a wind tunnel in the laboratory. The pressure in the test section ofthe wind tunnel is 1 atm = 1.01 × 105 N/m2. Calculate the necessaryvelocity, temperature, and density of the airflow in the wind-tunnel testsection such that the lift and drag coefficients are the same for thewind-tunnel model and the actual airplane in flight.
In an oil pool, a small steel ball is released from the surface (y=0) without initial velocity. The strength of the resistance force exerted by the oil against the movement of the ball is directly proportional to the speed of the ball (Fd = k*V , k: constant). Neglect the buoyant force exerted by the oil. (m = 0.2kg, k = 0.843550 kg/s, g = 9.81 m/s^2).
a-) What is the limit speed of ball ( Vlim)?
b-) What is the time it takes for the speed of the ball to reach 99% of the limit speed after it is released from the surface?
c-) What is the depth at which the ball's velocity reaches 99% of the limit velocity after it is released from the surface?
A one-third scale model of an airplane is to be tested in water. The airplane has a velocity of 900 km/h in air at −50°C. The water temperature in the test section is 10°C. The properties of air at 1 atm and −50°C: ? = 1.582 kg/m3, ? = 1.474 × 10−5 kg/m·s. The properties of water at 1 atm and 10°C: ? = 999.7 kg/m3, ? = 1.307 × 10−3 kg/m·s. In order to achieve similarity between the model and the prototype, the water velocity on the model should be (a) 97 km/h (b) 186 km/h (c) 263 km/h (d ) 379 km/h (e) 450 km/h
Chapter 1 Solutions
Fundamentals of Aerodynamics
Ch. 1 - For most gases at standard or near standard...Ch. 1 - Starting with Equations (1.7),(1.8), and (1.11),...Ch. 1 - Consider an infinitely thin flat plate of chord c...Ch. 1 - Consider an infinitely thin flat plate with a 1 m...Ch. 1 - Consider an airfoil at 12 angle of attack. The...Ch. 1 - Consider an NACA 2412 airfoil (the meaning of the...Ch. 1 - The drag on the hull of a ship depends in part on...Ch. 1 - The shock waves on a vehicle in supersonic flight...Ch. 1 - Consider two different flows over geometrically...Ch. 1 - Consider a Lear jet flying at a velocity of 250...
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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