Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 5, Problem 5.7P
Repeat Problem 5.6, except for a lower aspect ratio of 3. From a comparison of the results from these two problems, draw some conclusions about the effect of wing sweep on the lift slope, and how the magnitude of this effect is affected by aspect ratio.
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Students have asked these similar questions
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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Calculate the lift slope (in 1/rad) for a straight wing. (Round the final answer to three decimal places.)
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per radian.
Problem 06.002 - Calculate total drag
An airplane weighing 5,000 lb is flying at standard sea level
with a velocity of 525 mi/h. At this velocity, the L/D ratio is a
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The total drag on the airplane is
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CDo=0.020. e=1.0 (Oswald efficiency).
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(in
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_forwardChoose a specific airfoil for an airplane and determine the lift and drag forces after that calculate the power required to overcome drag. You must determine the following: The cruises speed and altitude. The aspect ratio.arrow_forwardUsing FOILSIM NASA -The basic shapes are symmetrical airfoil and flat platearrow_forward
- Task 2: An airplane with a NACA 662-215 airfoil cruises at 170 m/s at an altitude of 4550 m. The airfoil has an aspect ratio of 9 with a span of 30 m. Determine the lift and drag forces then determine the power required to overcome drag. Consider the airplane flying at an angle of attack equal to 2.arrow_forwardAn airplane with a NACA 23012 airfoil cruises at 150 m/s at an altitude of 6000 m. The airfoil has an aspect ratio of 10 with a span of 36 m. Using the airfoil data as in Fig. 3, determine the lift and drag forces. Then determine the power required to overcome drag. Consider the airplane flying at an angle of attack equal to 2.arrow_forwardTask 3arrow_forward
- Problem 05.021 - Calculate induced drag The Cessna Cardinal, a single-engine light plane, has a wing area of 16.2 m² and an aspect ratio of 7.31. Assume the span efficiency factor is 0.62. If the airplane is flying at standard sea- level conditions with a velocity of 290 km/h, what is the induced drag when the total weight is 9800 N? The induced drag when the total weight is 9800 N is N.arrow_forwardProblem 3 - A small airplane that has a mass of 1,500 lb,m is about to take off. The airplane has a coefficient of lift of 1.0 at an Angle of Attack (AOA) of zero and it linearly increases by 0.1 every 10 degrees; wings with a constant chord length of 3.5 ft and a total wingspan of 30 ft; a coefficient of drag of 0.3; and a frontal area of 40 ft? that linearly increases by 5 ft every 10 degrees. If the air is still, and the density of air is 0.076 lbm ft-3 at the ground level what is the critical speed needed for takeoff? If the runway is 1000 ft long, the total coefficient of friction between the road and the airplane is 0.25, what is the average thrust needed to achieve the critical takeoff speed?arrow_forwardConsider a positively cambered airfoil with a zero-lift angle of −3◦. The lift slope is 0.1 per degree. Now imagine the same airfoil turned upside-down, but at the same 5° angle of attack as part (a). Calculate the lift coefficient. (Round the final answer to one decimal place. You must provide an answer before moving on to the next part.) The lift coefficient is ............ At what angle of attack must the upside-down airfoil be set to generate the same lift as that when it is right-side-up at a 5° angle of attack? (Round the final answer to the nearest whole number.) The angle is ...........arrow_forward
- 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.arrow_forwardDescribe the downwash angle of a finite span wing and induced drag coefficient!arrow_forward6. For a wing of aspect ratio AR, having an elliptical lift distribution, the induced drag coefficient is (where CL is the lift coefficient) (b) TAR CL 2TAR (d) TAR2 (a) TAR 7. Laminar flow airfoil is used to reduce the (a) pressure drag (b) induced drag (c) skin friction drag (d) wave drag 8. Set the aerofoil your chosen angle of incidence is gives a good installed pressure distribution. (a) twelve degree (b) ten degree (c) eight degree 9. The critical Mach number for a thick airfoil will be (a) lesser than a thin airfoil. (b) greater than a thin airfoil. (c) equal to a thin airfoil. (d) cannot be related to thin airfoil 10. What is the dimension for Lift coefficient? (a) N/s (b) kg/N (c) Dimensionlessarrow_forward
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