Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 4, Problem 4.8P
Compare the results of Problems 4.6 and 4.7 with experimental data for the NACA 4412 airfoil, and note the percentage difference between theory and experiment. (Hint: A good source of experimental airfoil data is Reference 11.)
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Chapter 4 Solutions
Fundamentals of Aerodynamics
Ch. 4 - Consider the data for the NACA 2412 airfoil given...Ch. 4 - Consider an NACA 2412 airfoil with a 2-m chord in...Ch. 4 - Starting with the definition of circulation,...Ch. 4 - Starting with Equation (4.35), derive Equation...Ch. 4 - Consider a thin, symmetric airfoil at 1.5 angle of...Ch. 4 - The NACA 4412 airfoil has a mean camber line given...Ch. 4 - For the airfoil given in Problem 4.6, calculate...Ch. 4 - Compare the results of Problems 4.6 and 4.7 with...Ch. 4 - Starting with Equations (4.35) and (4.43), derive...Ch. 4 - For the NACA 2412 airfoil, the lift coefficient...
Ch. 4 - Consider again the NACA 2412 airfoil discussed in...Ch. 4 - For the airfoil in Problem 4.11, calculate the...Ch. 4 - In Section 3.15 we studied the case of the lifting...Ch. 4 - The question is often asked: Can an airfoil fly...Ch. 4 - The airfoil section of the wing of the British...Ch. 4 - For the conditions given in Problem 4.15, a more...
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- please answer do not image formatarrow_forwardIgn, McGraw-Hill, this chapter) and by New York, 1999, for more information. EXAMPLE 6.18 Estimate the landing ground roll distance at sea level for the CJ-1. No thrust reversal = 0. The spoilers increase the zero-lift, used; however, spoilers are employed such that L drag coefficient by 10 percent. The fuel tanks are essentially empty, so neglect the wejehr of any fuel carried by the airplane. The maximum lift coefficient, with flaps fully em ployed at touchdown, is 2.5.arrow_forwardProblem 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.)arrow_forward
- An airfoil has a lift curve slope at 7/rad and angle at zero lift of -3deg. At what angle of attack will the airfoil develop a lift of 120 lbs/ft at 110 mph under SSLC? Assume c = 10ft.arrow_forwardWhat does the coefficient of lift represent and why is it dimensionless? From the lift equation, which of the variables does the pilot control and how?arrow_forwardA conventional low speed aircraft had the following aerodynamic characteristics: CDo=0.020. e=1.0 (Oswald efficiency). The aircraft was flown to maintain a steady level flight and for minimum thrust required, at a lift coefficient of Cz=0.8. The numerical value of the aspect ratio of the wing is three decimal places). (inarrow_forward
- 1arrow_forwardA three-blade propeller of a diameter of 1.5 m has a rotational speed is 60 Hz, the activity factor AF is 200 and its static torque coefficient is 0.05. The propeller's integrated lift coefficient is 0.3.arrow_forwardA three-blade propeller of a diameter of 1.5 m has a rotational speed is 60 Hz, the activityfactor AF is 200 and its static torque coefficient is 0.05. The propeller’s integrated liftcoefficient is 0.3. If the aircraft’s lift to drag ratio is 10:1, calculate the requited thrust to weight ratio in orderto active a climb rate that is 8% of the flight speed.arrow_forward
- The test results of a NACA 2518 shows: Angle of attack 0 deg 8 deg CL 0.045 0.75 If the airfoil is used to construct a wing with a span of 60 ft and a wing area of 450 square feet. Determine the wing lift curve slope. (e = 0.88)arrow_forwardWhat is the total coefficient of a drag if at the maximum CL/Cd, the lift created is 60 lbs? The speed of the aircraft is 20 mph, and the area of the elliptical wing is 70 ft^2. The span of the wing is 20 ft. Assume standard sea level conditions.arrow_forwardThe drag polar equation of a light airplane in clean configuration can be written as Cp = 0.358 + 0.0405 C₁². It has a weight of 18,681 N. The wing area is 14.41 m². Calculate the minimum power required in watts. (Round off answer with no decimal places, No units, No commas) Answer given: 1461792 A 5,000 lbs. aircraft has an excess power of 75 hp at sea level. If the service ceiling is 3,657.6 m, determine the time to climb from sea level to absolute ceiling in minutes. (Round off answer with no decimal places. No units, No commas) Answer given: 17arrow_forward
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