Applied Fluid Mechanics (7th Edition)
7th Edition
ISBN: 9780132558921
Author: Robert L. Mott, Joseph A. Untener
Publisher: PEARSON
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Chapter 17, Problem 17.15PP
To determine
Percentage reduction in drag force.
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Problem 06.002 - Calculate total drag
An airplane weighing 5,000 lb is flying at standard sea level
with a velocity of 525 mi/h. At this velocity, the L/D ratio is a
maximum. The wing area and aspect ratio are 200 ft² and 8.5,
respectively. The Oswald efficiency factor is 0.93. Calculate
the total drag on the airplane. Assume poo = 0.002377 slug/ft³.
The total drag on the airplane is
lb.
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The image
below is a cross-section of a Darrieus-type and
wind turbine. Find the cross Sectional moment
provided by the bottom airfoil under the following
circumstances.
Calculate the lift coefficient based on the formula
CL = 27 (α -αL=c) Assume that stall is not
occuring
The airfoil has a zero lift angle of attack of O
degrees and a sectional drag coefficient of 7x10-
-3
10 = 41-7 RPM
6 = 13 degrees
R = 188 m
V = limls
C =017 m
Airdensity = 0.91 kg/m3
Find moment in N.m
C
R
co
C
Problem 06.025 - Calculate maximum velocity
The Predator UAV has the following characteristics: wingspan
= 14.85 m, wing area = 11.45 m², maximum weight = 1110 kgf,
and fuel weight = 295 kgf. The power plant is a Rotax four-
cylinder, four-stroke engine of 100 horsepower driving a two-
blade, variable-pitch pusher propeller. Assume: the Oswald
efficiency factor is 0.7; the zero-lift drag coefficient is 0.03; the
propeller efficiency is 0.9; and the specific fuel consumption is
0.2 kgf of fuel per horsepower per hour. Calculate the
maximum velocity of the Predator at sea level.
The maximum velocity of the Predator UAV at sea level is
m/s.
Chapter 17 Solutions
Applied Fluid Mechanics (7th Edition)
Ch. 17 - A cylinder 25 mm in diameter is placed...Ch. 17 - As part of an advertising sign on the top of a...Ch. 17 - Determine the terminal velocity (see Section 2.6.4...Ch. 17 - Calculate the moment at the base of a flagpole...Ch. 17 - A pitcher throws a baseball without spin with a...Ch. 17 - A parachute in the form of a hemispherical cup 1.5...Ch. 17 - Calculate the required diameter of a parachute in...Ch. 17 - A ship tows an instrument in the form of a 30...Ch. 17 - A highway sign is being designed to withstand...Ch. 17 - Assuming that a semitrailer behaves as a square...
Ch. 17 - A type of level indicator incorporates four...Ch. 17 - Prob. 17.12PPCh. 17 - A bulk liquid transport truck incorporates a...Ch. 17 - A wing on a race car is supported by two...Ch. 17 - Prob. 17.15PPCh. 17 - The four designs shown in Fig. 17.16 for the cross...Ch. 17 - Prob. 17.17PPCh. 17 - Prob. 17.18PPCh. 17 - An antenna in the shape of a cylindrical rod...Ch. 17 - Prob. 17.20PPCh. 17 - Prob. 17.21PPCh. 17 - Prob. 17.22PPCh. 17 - Assume that curve 2 in Fig. 17.5 is a true...Ch. 17 - Prob. 17.24PPCh. 17 - Prob. 17.25PPCh. 17 - A small, fast boat has a specific resistance ratio...Ch. 17 - Prob. 17.27PPCh. 17 - Assume that Fig. 17.11 shows the performance of...Ch. 17 - Calculate the total drag on an airfoil that has a...Ch. 17 - Prob. 17.30PPCh. 17 - Prob. 17.31PPCh. 17 - Prob. 17.32PPCh. 17 - Prob. 17.33PP
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- Calculate the lift and moment coefficients using thin airfoil theory approximations for a range of angle of attacks for the following airfoils below. 1. NACA 0008 2. NACA 0018 3. AG04 4. Clark-Y 5. NACA 2415 Angle of attacks taken to be between 0 degree to 15 degree. Also calculate value of Cm at quarter chord. (Cm at 0.25c) for each. Reynolds number 1000000arrow_forwardCompute for the lift force acting on a wing with an area of 56 sq. ft., velocity of 75 ft/s at an altitude of 5000 ft. Cl of the wing is 0.75. Calculate the drag of a certain wing with an area of 20 sq. meters , velocity of 75 m/s at an altitude of 2000m . Cd of the wing is 0.05. Compute for the drag of a rectangular wing with a chord of 4.5 ft and a span of 16 ft. if the dynamic pressure 80 psi. Cd of the wing is 0.030.arrow_forwardQ.17. A Kite Weighing 9.8 N and having an area 1 m makes an angle of 7° to horizontal when flying in a wind of 386 km/h. If pull on the string attached to the kite is 49 N and it is inclined to the horizontal at 45°. Calculate the lift and drag coefficients. Take p for air = 1.2 kg/arrow_forward
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