Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 1, Problem 1.19P
For the design of their gliders in 1900 and 1901, the Wright brothers used the Lilienthal Table given in Figure 1.65 for their aerodynamic data. Based on these data, they chose a design angle of attack of 3 degrees, and made all their calculations of size, weight, etc., based on this design angle of attack. Why do you think they chose three degrees?
Hint: From the table, calculate the ratio of lift to drag, L/D, at 3 degrees angle of attack, and compare this with the lift-to-drag ratio at other angles of attack. You might want to review the design box at the end of Section 1.8, especially Figure 1.36, for the importance of L/D.
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1. A simply supported shaft is shown in Figure 1 with wo = 25 N/cm and M = 20 N cm. Use
singularity functions to determine the reactions at the supports. Assume EI = 1000 kN cm².
M
Wo
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80 90
100 110 cm
Figure 1 - Problem 1
2. A support hook was formed from a rectangular bar. Find the stresses at the inner and outer
surfaces at sections just above and just below O-B.
210 mm
A distillation column with a total condenser and a partial reboiler is separating ethanol andwater at 1.0 atm. Feed is 0.32 mol fraction ethanol and it enters as a saturated liquid at 100mol/s on the optimum plate. The distillate product is a saturated liquid with 80 mol% ethanol.The condenser removes 5615 kW. The bottoms product is 0.05 mol fraction ethanol. AssumeCMO is valid.(a) Find the number of equilibrium stages for this separation. [6 + PR](b) Find how much larger the actual reflux ratio, R, used is than Rmin, i.e. R/Rmin. [3]Note: the heats of vaporization of ethanol and water are λe = 38.58 and λw = 40.645
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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