Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Textbook Question
Chapter 5, Problem 5.5P
Consider the airplane and flight conditions given in Problem 5.4. The span efficiency factor e for the complete airplane is generally much less than that for the finite wing alone. Assume
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Problem 7:
A small light plane with a wing area of 150ft² is cruising at 120mph at 7000ft altitude. The
airplane weighs 1600lb. Determine the lift coefficient. If the drag coefficient is 0.029, what is
the drag force in pounds? The air density, p, at 7000ft altitude is 0.001927 slugs/ft³. (Hint: In
level flight, assume lift equals weight.)
The lift on a spinning circular cylinder in a freestream with a velocity of 22 m/s and at standard sea level conditions is 6
N/m of span. Calculate the circulation around the cylinder.
The Drag Polar Equation of an General Aviation Aircraft in clean configuration can be written as:
C2
Cp = 0.0270+
%3D
32.787
Its weight is 2300 lb and the wing area is 155ft?, Calculate the (L/D)max and the Minimum Thrust Required
(Unaccelerated Level flight and Sea level Condition)
Chapter 5 Solutions
Fundamentals of Aerodynamics
Ch. 5 - Consider a vortex filament of strength in the...Ch. 5 - Consider the same vortex filament as in Problem...Ch. 5 - The measured lift slope for the NACA 23012 airfoil...Ch. 5 - The Piper Cherokee (a light, single-engine general...Ch. 5 - Consider the airplane and flight conditions given...Ch. 5 - Consider a finite wing with an aspect ratio of 6....Ch. 5 - Repeat Problem 5.6, except for a lower aspect...Ch. 5 - In Problem 1.19 we noted that the Wright brothers,...Ch. 5 - Consider the Superrnarine Spitfire shown in Figure...Ch. 5 - If the elliptical wing of the Spitfire in Problem...
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