Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 5, Problem 5.6P
Consider a finite wing with an aspect ratio of 6. Assume an elliptical lift distribution. The lift slope for the airfoil section is 0.1/degree. Calculate and compare the lift slopes for (a) a straight wing, and (b) a swept wing, with a half-chord line sweep of 45 degrees.
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Consider a finite wing with an aspect ratio of 3. Assume an elliptical liftdistribution. The lift slope for the airfoil section is 0.1/degree. Calculateand compare the lift slopes for (a) a straight wing, and (b) a swept wing,with a half-chord line sweep of 45 degrees.
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Consider a finite wing with an aspect ratio of 5. Assume an elliptical lift distribution. The lift slope for the airfoil section is
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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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- Consider a finite wing with an aspect ratio of 5. Assume an elliptical lift distribution. The lift slope for the airfoil section is 0.1/degree. Identify the correct statement about the lift slopes for the straight wing and the swept wing with a half-chord line sweep of 45 degrees. Multiple Choice A swept wing with a half-chord line sweep of 45 degrees has a slightly more lift slope than a straight wing. A swept wing with a half-chord line sweep of 45 degrees has a substantially more lift slope than a straight wing. A swept wing with a half-chord line sweep of 45 degrees has a slightly less lift slope than a straight wing. A swept wing with a half-chord line sweep of 45 degrees has a substantially less lift slope than a straight wing.arrow_forwardConsider a finite wing with an aspect ratio of 5. Assume an elliptical lift distribution. The lift slope for the airfoil section is 0.1/degree. Calculate the lift slope (in 1/rad) for a straight wing. (Round the final answer to three decimal places.) The lift slope for a straight wing is per radian.arrow_forwardConsider a thin, symmetric airfoil at 1.5◦ angle of attack. From the resultsof thin airfoil theory, calculate the lift coefficient and the momentcoefficient about the leading edge.arrow_forward
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- Consider the North American P-51D Mustang. Its wingspan is 37 ft; wing area is 233.6 ft2; and gross weight is 10,100 lb. Assume the Oswald efficiency factor as 0.8. The airplane is flying in steady; level flight at a velocity of 750 mi/h at a standard altitude of 5000 ft. Calculate the drag due to lift using the concept of span loading.arrow_forwardA wing has a planform area S of 200 ft? and a total span b of 40 feet. The airfoils are symmetric all along the span. The airfoil has a 2-D lift curve slope of 27 per radian. The wing has a rectangular planform, and thus has zero taper. The wing is untwisted. a. Compute the lift coefficient C and the drag coefficient Coi at an angle of attack of 4 degrees. Use two terms in the series expansion for circulation. T= 2bV,[4, sin ø + A, sin 3ø] b. Repeat the above calculation, now with just one term T=2bVA1sino. Compare the lift drag coefficient C and Cp values to problem #2 above. c. Compare the results for drag coefficient from part (b) above with that for an elliptically loaded wing at this lift coefficient.arrow_forwardFor a 10 deg included angle wedge at 0 deg AOA, calculate the lift and drag coefficient (Cl = 0, Cd = 0.082). Then calculate the lift and drag at AOA=4 deg (Cl = 0.16, Cd = 0.093). Let M=2.arrow_forward
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