Rotating cylinders were proposed as a means of ship propulsion in 1924 by the German engineer, Flettner. The original Flettner rotor ship had two rotors, each about 10 ft in diameter and 50 ft high, rotating at up to 800 rpm. Calculate the maximum lift and drag forces that act on each rotor in a 30-mph wind. Compare the total force to that produced at the optimum L / D at the same wind speed. Estimate the power needed to spin the rotor at 800 rpm.
Rotating cylinders were proposed as a means of ship propulsion in 1924 by the German engineer, Flettner. The original Flettner rotor ship had two rotors, each about 10 ft in diameter and 50 ft high, rotating at up to 800 rpm. Calculate the maximum lift and drag forces that act on each rotor in a 30-mph wind. Compare the total force to that produced at the optimum L / D at the same wind speed. Estimate the power needed to spin the rotor at 800 rpm.
Rotating cylinders were proposed as a means of ship propulsion in 1924 by the German engineer, Flettner. The original Flettner rotor ship had two rotors, each about 10 ft in diameter and 50 ft high, rotating at up to 800 rpm. Calculate the maximum lift and drag forces that act on each rotor in a 30-mph wind. Compare the total force to that produced at the optimum L/D at the same wind speed. Estimate the power needed to spin the rotor at 800 rpm.
Airplanes usually use their wings to turn: When the plane is tilted at an angle 0, the lift (L) from the wings provides a
vertical component and a horizontal component. The direction of the lift is in the plane of symmetry of the plane (up from
the wings). Suppose that the plane is tilted at an angle 0 = 29.0° and that it is making an exactly horizontal, circular path
at a uniform speed of 455 kph. Take g = 9.80 m.s2 for three significant figures (the value at Sydney).
What is the radius of its turn?
km.
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1. An airplane weighs 36,000 lb. and has a wing area of 450 fte. The drag equation is C, =0.014 + 0.05C} . It is
desired to equip this airplane with turboprop engines with available power such that a maximum speed of
602.6 mph at sea level can be reached. The available power is assumed to be independent of flight speed.
Calculate the maximum rate of climb and the speed at which it occurs.
Given:
W = 36,000 lb
S = 450 ft²
C, = 0.014+0.05C
V = 602.6 mph
max
THPy = cons tan t
THP
AV
constant
Max EHP
Point of THP,
REQD.
Flisht Speed. V
Vmax 602.6 mph
Required:
Max R.C. and Vmax R.C.
Horsepower, hp
1. A piston-prop aircraft has a wing loading of 1600 N/m², wing area of 25 m² and
its drag polar is given by Cp
1.5. The reciprocating engine develops 750 kW at sea level, and the propulsive
efficiency of the engine-propeller combination is 0.85. Draw the power-available
and power-required curves at sea level. Determine the maximum and minimum
speeds for level flight at sea level. What is the minimum power required for level
flight at sea level? Determine the corresponding velocity and lift coefficient.
0.025 + 0.05C. The maximum lift coefficient is
Chapter 9 Solutions
Fox and McDonald's Introduction to Fluid Mechanics
INTERNATIONAL EDITION---Engineering Mechanics: Statics, 14th edition (SI unit)
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