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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- Ign, 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_forwardA NACA 2412 airfoil with a chord of 0.64m is flying in an airstream of standard sea level conditions. The freestream velocity is 70 m/s. Given the lift per unit span is 1,254 N/m. By using the experimental data for NACA 2412 data plot in Figure Q1c, investigatethe angle of attack of the airfoil and the analyze the value of drag per unit spanof the airfoil. Given that at standard sea level, ?=1.789×10-5 kg/m.s.arrow_forwardEstimate the landing ground roll distance at sea level for the CJ-1. No thrust reversal is used; however, spoilers are employed such that L drag coefficient by 10 percent. The fuel tanks are essentially empty, so neglect the weight of any fuel caried by the airplane. The maximum lift coefficient, with flaps fully em- ployed at touchdown, is 2.5. 0. The spoilers increase the zero-lift,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_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
- A 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_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_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_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_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
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