Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Textbook Question
Chapter 4, Problem 4.12P
For the airfoil in Problem 4.11, calculate the value of the circulation around the airfoil.
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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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- Choose 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 span. The angle of attack.arrow_forwardAn 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_forwardQuestion 2: Consider the 5000kg aircraft below being in a 1000m radius looping maneuver (Fig.2). There are 4 forces acting on the aircraft (Weight, Thrust, Lift, Drag). Assuming that they are all approximately perpendicular to eachother at points A,B,C, calculate the following: A. Calculate the Lift Forces at points A, B, C if the aircraft was at a constant speed of 350km/h throughout the maneuver. B. Calculate the Lift Forces at points A, B, C if the aircraft starts the maneuver at point A at a speed of 400km/h, but reduces its speed with constant acceleration so that the pilot feels weightless at point C. C. A human can withstand earth's gravity was more than 9 times what it is now, we would not survive. What is the maximum of 9 times the gravitational acceleration, i.e. if the maximum speed the pilot can enter this maneuver? Figure 2: Looping Aircraftarrow_forward
- Aerodynamic Model: - Circular Disk Inside Dia.= 40 mm Outside Dia.= 80 mm Angle of Attack= 15 Degree Lift Force= 0.38 N Drag Force=0.40 N Wind Velocity= 20 m/sec Air Temperature= 30 oC (Note: Take Air Density at 30 oC) Required: - Find Lift and Drag Coefficient at 15 Degree Attack Angle.arrow_forwardAn airfoil is at 1,300 m with a freestream velocity of 50 m/s (incompressible). Calculate the following a. The total pressure b. The static pressure when the air velocity is 70 m/sarrow_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
- Air at a temperature of 15°C and a pressure of 1 Atm at a speed of 100 km / h figure below-a da it crashes into the visible water tower. Free at Figure-b to prevent Tower toppling as seen in the object diagram, the moment(M)that the base of the tower must resist calculate. The resistance coefficient for the cylinder part is 0.7, the resistance coefficient for the sphere part is 0.3 you may take.arrow_forwardIf the pressure difference in the wind tunnel experiment is 50 mmH,0, the density of air is 1.2 kg/m in wind tunnel experiment, and the airfoil span is 204 mm, and the cord length is 98 mm, what is the lift coefficient if the lift force is L=13.4 Narrow_forwardDerive a general expression to find circulation and the lift force for NACA 27014arrow_forward
- An aircraft is required to climb with 10° of climb angle. The aircraft has a mass of 30,000 kg and produces 50,000 N of drag. Assume zero angle of attack and zero thrust setting angle. How much thrust the aircraft engine must produce?arrow_forwardAn airfoil has a chord equal to 2 m. The center of pressure is located at the 40% of the chord from the leading edge. The resultant aerodynamic force R = 10 N, and acts in the direction such that angle \theta = 85 deg. Calculate the aerodynamic moment around the quarter-chord point (Mc/4), the leading edge (MLE), and the trailing edge (MTE)? (When calculating moments, indicate the sign “+” or “-”.)arrow_forwardAn aircraft is required to climb with 10° of climb angle. The aircraft has a mass of 30,000 kg and produces 50,000 N of drag. Assume zero angle of attack and zero thrust setting angle. How much lift this aircraft must generate?arrow_forward
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