Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 1, Problem 1.5P
Consider an airfoil at
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A 17,000-kg tractor-trailer rig has a frontal area of 9.2 m2, a drag coefficient of 0.96, a rolling resistance coefficient of 0.05 (multiplying the weight of a vehicle by the rolling resistance coefficient gives the rolling resistance), a bearing friction resistance of 350 N, and a maximum speed of 110 km/h on a level road during steady cruising in calm weather with an air density of 1.25 kg/m3. Now a fairing is installed to the front of the rig to suppress separation and to streamline the flow to the top surface, and the drag coefficient is reduced to 0.76. Determine the maximum speed of the rig with the fairing.
A commercial airplane has a total mass of 70,000 kg and a wing planform area of 150 m2. The plane has a cruising speed of 558 km/h and a cruising altitude of 12,000 m, where the air density is 0.312 kg/m3. The plane has double-slotted flaps for use during takeoff and landing, but it cruises with all flaps retracted. Assuming the lift and the drag characteristics of the wings can be approximated by NACA 23012 , determine (a) the minimum safe speed for takeoff and landing with and without extending the flaps, (b) the angle of attack to cruise steadily at the cruising altitude, and (c) the power that needs to be supplied to provide enough thrust to overcome wing drag.
A small aircraft has a wing area of 37 m2, a lift coefficient of 0.45 at takeoff settings, and a total mass of 4300 kg. Determine the following:
The takeoff speed of this aircraft at sea level at standard atmospheric conditions
The wing loading
The required power to maintain a constant cruising speed of 300 km/h for a cruising drag coefficient of 0.036
Chapter 1 Solutions
Fundamentals of Aerodynamics
Ch. 1 - For most gases at standard or near standard...Ch. 1 - Starting with Equations (1.7),(1.8), and (1.11),...Ch. 1 - Consider an infinitely thin flat plate of chord c...Ch. 1 - Consider an infinitely thin flat plate with a 1 m...Ch. 1 - Consider an airfoil at 12 angle of attack. The...Ch. 1 - Consider an NACA 2412 airfoil (the meaning of the...Ch. 1 - The drag on the hull of a ship depends in part on...Ch. 1 - The shock waves on a vehicle in supersonic flight...Ch. 1 - Consider two different flows over geometrically...Ch. 1 - Consider a Lear jet flying at a velocity of 250...
Ch. 1 - A U-tube mercury manometer is used to measure the...Ch. 1 - The German Zeppeins of World War I were dirigibles...Ch. 1 - Consider a circular cylinder in a hypersonic flow,...Ch. 1 - Derive Archimedes principle using a body of...Ch. 1 - Consider a light, single-engine, propeller-driven...Ch. 1 - Consider a flat plate at zero angle of attack in a...Ch. 1 - Consider the Space Shuttle during its atmospheric...Ch. 1 - The purpose of this problem is to give you a feel...Ch. 1 - For the design of their gliders in 1900 and 1901,...Ch. 1 - Consider the existence of a forward-facing axial...
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- 13.94. A body travels through 60° standard air at 60 mph, and 5.5 hp is required to maintain this speed. If the projected area is 13.5 ft2 , find the drag coefficient. Ans. 0.28arrow_forwardConsider an airfoil at 12◦ angle of attack. The normal and axial forcecoefficients are 1.2 and 0.03, respectively. Calculate the lift and dragcoefficients.arrow_forwardName some applications in which a large drag is desired.arrow_forward
- 22. What is lift force? Explain the lift coefficient23. What is the drag force? Explain the drag coefficient Plot their graphicsarrow_forwarddiscuss various designs of winglets to reduce induced drag.arrow_forwardThe drag coefficient of a car at the design conditions of 1 atm, 70°F, and 60 mi/h is to be determined experimentally in a large wind tunnel in a full-scale test. The frontal area of the car is 22.26 ft2. If the force acting on the car in the flow direction is measured to be 68 lbf, determine the drag coefficient of this car.arrow_forward
- The 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_forwardHow does the Reynolds number effect the lift and drag coefficient for a symmetrical airfoilarrow_forwardAn airplane has a mass of 50,000 kg (without load), a wing area of 360 m2 , a maximum lift coefficient of 3.25, and a cruising drag coefficient of 0.03 at an altitude of 12,000 m. Taking the density of standard air as ρ1 = 1.225 kg/m3 at sea level and ρ2 = 0.312 kg/m3 at 12,000 m altitude. (a) Generate a plot of the safe takeoff speed at sea level Vs the load carried by airplane (ranging from 0 kg to 20,000 kg of load). (b) Determine the power that must be delivered by the engines for a cruising speed of 800 km/hr.arrow_forward
- An airplane is cruising at a velocity of 950 km/h in air whose density is 0.526 kg/m3. The airplane has a wing planform area of 90 m2. The lift and drag coefficients on cruising conditions are estimated to be 2.0 and 0.06, respectively. The power that needs to be supplied to provide enough trust to overcome wing drag is (a) 21,500 kW (b) 19,300 kW (c) 23,600 kW (d ) 25,200 kW (e) 26,100 kWarrow_forwardA 0.25 kg kite with an area of 0.65 mitres squared flies in a 25 km/h wind such that the weightless string makes an angle of 40° relative to the horizontal.The density of air is 1.22 kg/m^3.if the pull on string is 7 N.determine the lift and drag coefficient basee on the kite areaarrow_forwardWhat is the Effect of wing plan form (taper ratio and wing twist) and aspect ratio(AR) on the Induced drag coefficient, ?arrow_forward
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