P5.72 A one-twelfth-scale model of a large commercial aircraft is tested in a wind tunnel at 20°C and 1 atm. The model chord length is 27 cm, and its wing area is 0.63 m?. Test results for the drag of the model are as follows: V, mi/h 50 75 100 125 Drag, N 15 32 53 80 In the spirit of Fig. 5.8, use this data to estimate the drag of the full-scale aircraft when flying at 550 mi/h, for the same angle of attack, at 32,800 ft standard altitude. Neglect Mach number differences between model and prototype.

P5.72 A one-twelfth-scale model of a large commercial aircraft is tested in a wind tunnel at 20°C and 1 atm. The model chord length is 27 cm, and its wing area is 0.63 m?. Test results for the drag of the model are as follows: V, mi/h 50 75 100 125 Drag, N 15 32 53 80 In the spirit of Fig. 5.8, use this data to estimate the drag of the full-scale aircraft when flying at 550 mi/h, for the same angle of attack, at 32,800 ft standard altitude. Neglect Mach number differences between model and prototype.

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Related questions

Q: The traditional "Moody-type" pipe friction correlation in Chap. 6 is of the form 2APD f = pVL (pVD и…

A: PART A- Given that,

Q: A student wants to estimate drag force on a golf ball of diameter D moving in air at a speed of U at…

A: GivenFor golf balldiameter D speed Urepilcadiameter d=D5speed u=5U

Q: A diamond-shaped body, of characteristic length 9 in, hasthe following measured drag forces when…

A: The properties of the air at the sea level are: The properties of air at 20 degrees Celsius are:…

Q: 7.21. A model of a thin streamlined body is placed in a flow for testing. The body is 0.9 m (3 ft)…

Q: Q5: A prototype ship is 35 m long and designed to cruise at 11 m/s. Its drag is to be simulated by a…

Q: 2) A prototype ship is 50 m long and designed for cruising speed of 10 m/s. The drag is to be…

Q: Q3: A steam power plant operates on an ideal regenerative Rankine cycle with two open feedwater…

Q: aerodynamic derivative X, may be determined from the following expression: X =-pU SCD %3D nere pis…

A: Answer is given below:

Q: Chapter 4 1. Solve for parsite drg with air denaity 9, velocity 10 KIAS, Car13, urface area 174 2…

Q: How much is the max available power (in Kg) of a scraper Caterpillar 651E whose weight and maximum…

Q: A 30 cm diameter cork ball (S=0.21) is tied to the bottom of a river as shown. (a) Draw the free…

Q: A long, slender, smooth 3-cm-diameter flagpole bendsalarmingly in 20 mi/h sea-level winds, causing…

A: Given data: The diameter flagpole is D = 3 cm = 0.03 m The speed of wind is v = 20 mi/h Since, 1…

Q: A propeller driven aircraft has the following parabolic non-dimensional drag curve: CD = 0.015 +…

Q: A hydrofoil 51 cm long 4 m wide moves at 1m/s in water at temperature 20 C. Use laminar boundary…

A: Given Data⇒ Length of the hydrofoil is L=51 cm L=0.51 m w=4 m Velocity is v=1ms At T=200C Laminar…

Q: The drag of an airfoil (Fig.) increases considerably ifyou turn the sharp edge around 180° to face…

A: When the sharp edge of the airfoil is turned around by 180 degrees, the t/c ratio increases. From…

Q: Show by dimensional analysis that this leads to the loga rithmic overlap relation (6.28). The…

A: Given DataT=24°Cair Density and kinematic viscosity at 24°C from dataρ=1.225kg/m3ϑ=1.543m2/s

Q: need of Fair is su s 310 m

Q: GIVEN A thin rectangular plate having a width w and a height h is located so that it is normal to a…

Q: Q4. Consider an aircraft flying in straight and level flight with total wing area 110 m², wing…

A: Apply the energy equation for rising flight in order to determine the climb rate that the aircraft…

Q: A golf ball weighs 0.102 lbf and has a diameter of 1.7 in.A professional golfer strikes the ball at…

A: Given: The mass of golf ball, m = 0.102 kg The diameter of the golf ball, d = 1.7 in The initial…

Q: To measure the drag of an upright person, without violatinghuman subject protocols, a life-sized…

A: Write the given data: pair=1.2 kg/m3L=6 mN=80 rpmP=60 kW=60000W1000 W1 kW

Q: An aircraft weight 980 kN flying steady and level at true airspeed of 720 km/hr at sea level. The…

Q: The drag equation of an aircraft is given by the equation: Cp = 0.025 + 0.035 CZ The weight of the…

A: Given dataW=120kNA=32m2F=12kNUsing the Drag relation then equation to find speed

Q: expression coe7zicient of Drag and coe77icient 07 moment using Denive on For for dimensional…

A: The pressure distribution on the wing determines lift and drag. The shape of the airfoil, the…

Q: Inside a ship building R&D center, a model of a ship was to be put under experimental analysis, for…

A: A ship-building R&D center-Length ratio Lm/Lp=1/25The speed of the actual full-scale ship is…

Q: A 1:20 scaled-down model of a hydrofoil is tested in a water channel, at a velocity of 0.179 m/s. At…

Q: 20 4. An airship is to operate at 20 m/s in air at standard conditions (p 1.225 kg/m³, p 101,300…

A: 1.2.

Q: A baseball is thrown directly upward (in z direction) from the ground (z = 0) with some initial…

A: When a baseball is thrown vertically upward with initial velocity then it goes up to a certain…

Q: Aerodynamics NACA 747A415, chord is 180 cm 1) What is the location of favorable pressure gradient of…

Q: An aircraft flying steady and level at true airspeed of 720 km/hr at sea level. The aircraft have…

A: Given that, Velocity of aircraft = V=720 km/hr=200 m/s Wing area of aircraft = S=187 m2 Thrust of…

Q: Select an appropriate set of variables that influence the drag force FD on an airfoil (Fig. P6.23)…

Q: A small, axisymmetric, low-speed wind tunnel is built to calibrate hot wires. The diameter of the…

A: At 60°F The properties of air ρ=0.07489 lbm/ft3μ=1.23×10-5 lbm/ft.s The speed of air, v=5 ft/s…

Q: Show by dimensional analysis that this leads to the loce rithmic overlap relation (6.28). The…

A: Given DataT=24°Ckinematic viscosityϑ=1.543×10-5m3/sDensityρ=1.225kg/m3

Q: The drag force (Fdrag) exerted by air on a moving car depends on a dimensionless drag coefficient…

Q: uniform stream overflows in a circular cylinder and then a periodic Kármán vortex street is created.…

A: Use Buckingham pi method to solve this problem

Q: The drag force, F, imposed on the horizontal axis wind turbine with wind speed of 20 m/s, blade…

Q: When tested in water at 20 ° C fl owing at 2 m/s, an 8 - cmdiametersphere has a measured drag of 5…

A: Given data V=2 m/secρw=998 kg/m3μw=1×10-3 pa·sec For prototype dp=1.5 mρa=1.2 kg/m3μa=1.8×10-5…

Q: A 30 cm diameter cork ball (S=0.21) is tied to the bottom of a river as shown. (a) Draw the free…

Question

100%

P5.72
A one-twelfth-scale model of a large commercial aircraft is tested in a
wind tunnel at 20°C and 1 atm. The model chord length is 27 cm, and its wing area is
0.63 m?. Test results for the drag of the model are as follows:
V, mi/h
50
75
| 100
125
Drag, N
15
| 32
53
80
In the spirit of Fig. 5.8, use this data to estimate the drag of the full-scale aircraft when
flying at 550 mi/h, for the same angle of attack, at 32,800 ft standard altitude. Neglect
Mach number differences between model and prototype.

Expert Solution

This question has been solved!

Explore an expertly crafted, step-by-step solution for a thorough understanding of key concepts.

This is a popular solution!

SEE SOLUTION Check out a sample Q&A here

Step 1

Step 2

Step 3

Step 4

Step 5

Step 6

Trending now

This is a popular solution!

Step by step

Solved in 6 steps with 6 images

SEE SOLUTION Check out a sample Q&A here

Knowledge Booster

Learn more about

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

Q.3 Air (density 1.2 kg/m3 and kinematic viscosity 15 centistokes) flows over a flat plate, at zero angle of incidence, at a velocity of 20 m/s. If Reynolds number at transition is taken as 2.5 × 105, maximum distance, from leading edge up to which the boundary layer remains laminar is
Solve it from 1 to 4 PLZ
A prototype ship is 50 m long and designed for cruising speed of 10 m/s. The drag is to be simulated by a 1-m-long model that will be towed in a towing tank. Using Froude scaling, determine the tow speed and the ratio of the model to prototype drag and power.
fluid mechanics 1
Some engineers want a good estimate of drag and boundary-layerthickness at the trailing edge of a miniature wing. The chord and span ofthe wing are 6 mm and 30 mm, respectively and a typical flight speed is5 m/s in air (kinematic viscosity = 15 × 10−6 m2/s; density = 1.2kg/m3). An engineer may decide to make a superseding model withchord and span of 150 mm and 750 mm, respectively. Measurements onthe model in a water channel flowing at 0.5 m/s (kinematic viscosity = 1× 10−6 m2/s, density = 1000 kg/m3) give a drag of 0.19 N and aboundary-layer thickness of 3 mm. Estimate the corresponding values forthe prototype
2. The table below shows experimental data for the shape and pressure distribution on the upper and lower surface of an airfoil at zero angle of attack. X 0 0.25 0.5 0.75 1 Yu 0 0.0952 0.0922 0.0588 0 Fx = dYu dx 5 Y₁ 0 -0.0254 -0.0144 -0.0052 0 PL Pd) d: dx Y = Yu (x) Calculate the drag and lift force on the airfoil by numerically evaluating the integrals = S₁² ( P₂₁ = ['(P₁ - F (P₁ - Pu)dx 0 y = Y₂ (x) Pu 1.000 -1.640 -0.786 -0.212 0 Fy x Pi 1.000 0.589 0.426 0.322 0 Use finite difference approximations of the derivatives and the composite Simpson's rule to evaluate the integrals. Hint: Use central differences to estimate the derivatives wherever possible since they are more accurate than forward or backward differences.
In elementary mechanical fluid
Looking for correct answer within 30minutes.
The thrust F of a Free propeller, either aircraft of marine, depends upon density ρ, the rotation rate n in r/s, the diameter D, and the forward velocity V. Viscous effects are slight and neglected here. Tests of a 25-cm-diameter model aircraft propeller, in a sea-level wind tunnel, yield the following thrust data at a velocity of 20 m/s : Rotation Rate, r/min____4800____6000____8000 Measured thrust, N____6.1____19____47 Use the dimensionless data to predict the thrust, in Newtons, of a similar 1.6-m-diameter prototype propeller when rotating at 3800 r/min and flying at 225 mi/h at 4000-m standard altitude.
The drag on a 2-m-diameter satellite dish due to an 69-km/hr wind is to be determined through a wind tunnel test using a geometrically similar 0.4-m-diameter model dish. Assume standard air for both model and prototype. (a) At what air speed should the model test be run? (b) With all similarity conditions satisfied, the measured drag on the model was determined to be 152 N. What is the predicted drag on the prototype dish? (a) Vm = (b) D = i i km/hr N
Please please correct answer