2. The table below shows experimental data for the shape and pressure distribution on the upperand lower surface of an airfoil at zero angle of attack.X00.250.50.751YFx =Yu00.09520.09220.05880(PudYudx-Calculate the drag and lift force on the airfoil by numerically evaluating the integralsFy (P₁-P₂)dx= √ ( P₁ - 1PiY₁0-0.0254-0.0144-0.00520dv)Y = Yu (x)dxy = Ye (x)Pu1.000-1.640-0.786-0.2120xPi1.0000.5890.4260.3220Use finite difference approximations of the derivatives and the composite Simpson's rule toevaluate the integrals. Hint: Use central differences to estimate the derivatives whereverpossible since they are more accurate than forward or backward differences.

The central difference for the numerical derivatives are dYudx=Yui+1…

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 Oo Y Yu 0 0.0952 0.0922 Y₁ 0 -0.0254 -0.0144 Y= Yu (x) y = Ye (x) Pu 1.000 -1.640 -0.786 x Pi 1.000 0.589 0.426

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 Oo Y Yu 0 0.0952 0.0922 Y₁ 0 -0.0254 -0.0144 Y= Yu (x) y = Ye (x) Pu 1.000 -1.640 -0.786 x Pi 1.000 0.589 0.426

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

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Concept explainers

Metrology of surface finish

In general terms, the application of scientific principles in the study of measurements is known as metrology. When speaking about measurement, it could be of time, length, microstructures, grain structures, internal crystal discontinuities, surface roughness, measurements of angles, height, width, and so on. While coming to the domain of mechanical engineering, metrology is considered the science of measurements of surface finish, length, surface texture, and angles.

Question

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
Y
Fx =
Yu
0
0.0952
0.0922
0.0588
0
(Pu
dYu
dx
-
Calculate the drag and lift force on the airfoil by numerically evaluating the integrals
Fy (P₁-P₂)dx
= √ ( P₁ - 1
Pi
Y₁
0
-0.0254
-0.0144
-0.0052
0
dv)
Y = Yu (x)
dx
y = Ye (x)
Pu
1.000
-1.640
-0.786
-0.212
0
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.

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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.
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