Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 12, Problem 12.7P
Using the same flight conditions and the same value of the skin-friction coefficient from Example 12.3, and the results of Problem 12.6, calculate the maximum lift-to-drag ratio of the flat plate that is used to simulate the F-104 wing and the angle of attack at which it occurs.
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Chapter 12 Solutions
Fundamentals of Aerodynamics
Ch. 12 - Using the results of linearized theory, calculate...Ch. 12 - For the conditions of Problem 12.1, calculate the...Ch. 12 - Consider a diamond-wedge airfoil such as shown in...Ch. 12 - Equation (12.24). from linear supersonic theory....Ch. 12 - Consider a flat plate at an angle of attack in an...Ch. 12 - Consider a flat plate at an angle of attack in a...Ch. 12 - Using the same flight conditions and the same...Ch. 12 - The result from Problem 12.6 demonstrates that...
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- discuss various designs of winglets to reduce induced drag.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_forwardCalculate Induced Drag pleasearrow_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_forwardThe rectangular wings of a microlight aircraft have a combined spanwise length of 9.144 m and streamwise (direction of air flow) width of 0.9144 m The wings have a coefficient of form drag of 0.01 and a lift coefficient of 0.3 in cruise. When cruising at a speed of 150km/h and altitude of 3,000 feet, the temperature and absolute pressure of the atmospheric air are 5°C and 90 kPa, respectively.arrow_forwardThe maximum lift to drag ratio is 16:9. Calculate the minimum glide angle and maximum range measured along the ground covered in power off glide that starts at an altitude of 4000 feet.arrow_forward
- QUESTION 2 A streamlined experimental solar car has a frontal area of 0.48 m² and an expected coefficient of drag of 0.12. The car and driver have a total mass of 200 kg. What is the maximum speed that could be expected if the maximum power available from its electric motor is 350 W? Assume a rolling resistance coefficient of 0.015. Take the density of air as 1.21 kg/m³.arrow_forwardThe measured lift slope for the NACA 23012 airfoil is 0.1080 degree−1,and αL=0 = −1.3◦. Consider a finite wing using this airfoil, with AR = 8and taper ratio = 0.8. Assume that δ = τ . Calculate the lift and induceddrag coefficients for this wing at a geometric angle of attack = 7◦.arrow_forwardA flat plate has a surface roughness of 0.1 mm, a width of 3 m, and a length of 2 m. Air with a velocity of 3 m/s flows over the plate. a. Calculate the drag exerted on the plate if the flow at the leading edge of the plate is laminar. b. Calculate the drag exerted on the plate if the flow at the leading edge of the plate is immediately tripped to turbulence due to the presence of an exposed boltarrow_forward
- For the NACA 2412 airfoil, the lift coefficient and moment coefficient about the quarter-chord at -6° angle of attack are -0.39 and -0.045, respectively. At 4° angle of attack, these coefficients are 0.65 and -0.037, respectively. Calculate the location of the aerodynamic center. -arrow_forwarding 16. Consider a finite wing with aspect ratio A-8 and elliptical planform. The aerofoil section is thin and symmetric. Calculate the lift and induced drag coefficients when angle of attack is five degrees.arrow_forwardAlight aircraft with a wing area of 114 m^2 and a span of 29 m is flying at an altitude of 3,550 m when the engine suddenly fails. If the parasite drag coefficient is 0.0325, determine the maximum distance over the ground that the aircraft can cover. Assume elliptical lift distribution. Provide answer in km, nearest hundredths.arrow_forward
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