ENG ME 421 AERODYNAMICS >CUSTOM<
17th Edition
ISBN: 9781308966960
Author: Anderson
Publisher: MCG/CREATE
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Chapter 1, Problem 1.12P
The German Zeppeins of World War I were dirigibles with the following typical characteristics:
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Chapter 1 Solutions
ENG ME 421 AERODYNAMICS >CUSTOM<
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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Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, mechanical-engineering and related others by exploring similar questions and additional content below.Similar questions
- A propeller-driven aircraft has an in-flight weight of 4,105 lb (equivalent to a mass of 1,862 kg) and is cruising at a true airspeed of 120 kts. The lift-to-drag ratio of the aircraft is 8.2. If the propeller efficiency, ηp, is 0.8, then how much brake power is required for flight? Work through this problem in both USC and SI units.arrow_forwardThe so-called Rocket Man, Yves Rossy, fl ew across the Alps in2008, wearing a rocket-propelled wing-suit with the followingdata: thrust = 200 lbf, altitude = 8,200 ft, and wingspan = 8 ft(http://en.wikipedia.org/wiki/Yves_Rossy). Further assume awing area of 12 ft2, total weight of 280 lbf, CDq = 0.08 for thewing, and a drag area of 1.7 ft2 for Rocket Man. Estimate themaximum velocity possible for this condition, in mi/h.arrow_forwardAn airfoil generates a 1200 N/m sectional lift when traveling at 75 m/s at sea level. What is the circulation generated by this airfoil?arrow_forward
- Determine the velocity required for take off for an aircraft with the following characteristics.Aircraft mass: 7200 kgWingspan: 15 mWing shape: rectangularWing chord length: 1.8 mWing airfoil: NACA 4415Wing angle of attack: 7× 0.5 + 5 degreesHint: Check NACA charts for required parameters.arrow_forwardA 30 cm diameter cork ball (S=0.21) is tied to the bottom of a river as shown. (a) Draw the free body diagram of the ball. (b) Calculate the tension in the string and the drag force on the ball. (c) Estimate the speed, Uo of the river current Hint: Volume of a sphere = (1/6)πD³.arrow_forwardAerodynamics NACA 664-221 Chord c = 150 cm 1) What is the CL range to achieve the minimum coefficient of drag? 2) What is the thickness ratio of the airfoil?arrow_forward
- A tractor-trailer truck is coasting freely, with no brakes,down an 8° slope at 1000-m standard altitude. Rollingresistance is 120 N for every m/s of speed. Its frontalarea is 9 m2, and the weight is 65 kN. Estimate the terminalcoasting velocity, in mi/h, for (a) no deflector and(b) a deflector installed.arrow_forwardFor those who think electric cars are sissy, Keio University inJapan has tested a 22-ft-long prototype whose eight electricmotors generate a total of 590 horsepower. The “Kaz” cruisesat 180 mi/h (see Popular Science, August 2001, p. 15). If thedrag coefficient is 0.35 and the frontal area is 26 ft2, what percentageof this power is expended against sea-level air drag?arrow_forwardConsider a Boeing 747 airliner cruising at a velocity of 550 mi/h at a standard altitude of 38,000 ft, where the freestream pressure and temperature are 432.6 lb/ft2 and 390◦R, respectively. A one-fiftieth scale model of the 747 is tested in a wind tunnel where the temperature is 430◦R. In addition to the information given in above, for this airplane the zero-lift angle of attack is −2◦, the lift slope of the airfoil section is 0.1 per degree, the lift efficiency factor τ = 0.04, and the wing aspect ratio is 7.96. At the cruising condition treated given, calculate the angle of attack of the airplane.arrow_forward
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