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 17.23PP
Assume that curve
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q: An aircraft is flying straight and level at a certain altitude with a velocity of 214 fps. Determine the power required if the wing area is 115 ft? and the total drag coefficient is 0.067. Assume SSLC (p=0.002377 slug/ft3).
Provide answer in ft-Ib/s.
and round off to the nearest whole number.
Solve using standard English units.
A 1:20 scale down model of a hydrofoil is tested in a water channel, at
velocity of 0.179 m/s. At this velocity, a drag force of 2.2 N is measured.
Determine the drag force of the original hydrofoil, at velocity of 0.8 m/s.
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
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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- = 3570 T AC =144 Example: 1.5 ft It is desired to determine the drag force at a given speed on a prototype sailboat hull. A model is placed in a test channel and three cables are used to align its bow on the channel centerline. For a given speed, the tension is 40 lb in cable AB and 60 lb in cable AE. Flow 4 ft Determine the drag force exerted on the hull and the tension in cable AC. Choc ug the h- as the free hod- DApress thearrow_forward8.) A circular cylinder 4m long and 3m in diameter is in an air stream. The flow velocity is 5 m/s L parallel to the axis of the cylinder. Given that the coefficient of drag, CD on the cylinder is 1.3, and the density of air is 1.225 kg/m3. What is the force on the cylinder? A. 0.090 KN B. 0.14 KN C. 0.24 KN D. 0.91 kNarrow_forwardA blimp is designed to move in air at C at 7 m/s. If a 1:20 scale model is tested in water at 20 "C, what should the water velocity be? If the measured water drag on the model is 3.2kN, calculate the drag on the prototype blimp and the power required to propel it. (For water u 1.02x10 pa.s, p 1000 kg/m' and for air a 1.81x10 pa.s, p 1.2kg/m')arrow_forward
- 6.10 A sphere advancing at 1.5 m/s in a stationary mass of water experiences a drag of 4.5 N. Find the flow velocity required for dynamic similarity of another sphere twice the diameter, placed in a wind tunnel. Calculate the drag at this speed if the kinematic viscosity of air is 13 times that of water and its density is 1.25 kg/m³. Ans. (9.75 m/s, 0.951 N)arrow_forwardProblem 3: Let's say you want to predict the aerodynamic drag of a new car based on the use of a model that is one- fifth scale of the actual car/prototype car. We want to predict the drag of the car when it has wind velocity 75 miles/hour with an air temperature of 40°C. The model is placed in a wind tunnel at 10°C. Determine the wind tunnel velocity necessary to achieve similarity between the model and the prototype.arrow_forwardA helicopter is hovering at an altitude where the density of air is 1.165 kg/m³. The helicopter rotor disc has a diameter of 9 m and is rotating at 466 rpm, with the blades having a chord of 0.16 m. Estimate the drag force in newtons per unit span along an elemental strip at the mid-span of the blade. You may assume the drag coefficient of the blade at the mid-span is 0.025.arrow_forward
- Derive the expression for the drag on a submerged torpedo. The parameters are the size of torpedo, L, the velocity, V, the viscosity, and density of water, u and p respectively.arrow_forward04) Define the boundary layer, then find the thickness of boundary layer, shear stress, drag force and coefficient of drag in terms of Re for the velocity profile of laminar boundary layer u/U-4(y/6)-6(y/ö)5. Calculate the boundary layer thickness and drag force if the air flows over a sharp edged flat plate Im long and 0.5m wide at a velocity 0.9m/s, the air density 1.23 kg/m³ and the kinematic viscosity is 1.46*10-³ m/s².arrow_forwardA 1:20 scaled-down model of a hydrofoil is tested in a water channel, at a velocity of 0.179 m/s. At this velocity, a drag force of 2.2 N is measured. Determine the drag force of the original hydrofoil, at a velocity of 0.8 m/s.arrow_forward
- 3) An advertising sign mounted on the roof of a car is 33 inches tall, 15 inches wide and 54 inches long (airflow direction). The underside of the sign is flush with the top surface of the roof. Take air properties to be: p = 0.075 lbm/ft' and u= 1.22x10 lbm/ft.sec. Used a pressure drag coefficient of 1.2 for the advertisement sign. Calculate the total drag on the sign and the power required to overcome its effect if the car is travelling at a constant speed of a) 12 mph and b) 45 mph. Note: Provide a schematic diagram (sketch) of the problem configuration (if applicable). Every numerical calculation must be preceded by the appropriate equation. Do not forget units & dimensions during your calculations.arrow_forwardThe Drag Polar Equation of an General Aviation Aircraft in clean configuration can be written as: C2 Cp = 0.0270+ %3D 32.787 Its weight is 2300 lb and the wing area is 155ft?, Calculate the (L/D)max and the Minimum Thrust Required (Unaccelerated Level flight and Sea level Condition)arrow_forwardThe drag polar equation of a light airplane in clean configuration can be written as Cp = 0.358 + 0.0405 C₁². It has a weight of 18,681 N. The wing area is 14.41 m². Calculate the minimum power required in watts. (Round off answer with no decimal places, No units, No commas) Answer given: 1461792 A 5,000 lbs. aircraft has an excess power of 75 hp at sea level. If the service ceiling is 3,657.6 m, determine the time to climb from sea level to absolute ceiling in minutes. (Round off answer with no decimal places. No units, No commas) Answer given: 17arrow_forward
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