Given the following data Airfoil A Airfoil B Angle 20 15 10 5 0 Angle 20 15 10 5 0 Page 10 of F (N) 38.5 48.05 42.507 22.04 0 F (N) 50.75 57.4 48.8 25.95 0 The surface area of airfoil A is (length*width *2)= 0.194 sq. Meters The surface area of airfoil B is (length*width*2)= 0.210 sq. Meters v=62 km/h The dynamic pressure = 1 * p*v² p: density of air in kilograms per cubic metre (1.225Kg/m^3), v: velocity of air in mete second 1- Fill out the following table (Show your calculations) Lift Angle of attack coefficient (Airfoil 1) Lift coefficient (Airfoil 2) 2- Plot the lift Coefficient vs Angle for both airfoils, and discuss your findings. 3- Determine the stall angle of both airfoils. 4- Explain how the planes fly.
Given the following data Airfoil A Airfoil B Angle 20 15 10 5 0 Angle 20 15 10 5 0 Page 10 of F (N) 38.5 48.05 42.507 22.04 0 F (N) 50.75 57.4 48.8 25.95 0 The surface area of airfoil A is (length*width *2)= 0.194 sq. Meters The surface area of airfoil B is (length*width*2)= 0.210 sq. Meters v=62 km/h The dynamic pressure = 1 * p*v² p: density of air in kilograms per cubic metre (1.225Kg/m^3), v: velocity of air in mete second 1- Fill out the following table (Show your calculations) Lift Angle of attack coefficient (Airfoil 1) Lift coefficient (Airfoil 2) 2- Plot the lift Coefficient vs Angle for both airfoils, and discuss your findings. 3- Determine the stall angle of both airfoils. 4- Explain how the planes fly.
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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Question
Solve it from 1 to 4 PLZ
Transcribed Image Text:Task (VI) Wind Tunnel:
Given the following data
Airfoil A
Airfoil B
Angle
20
15
10
5
0
Angle
20
15
10
5
0
Page 10 of
F (N)
38.5
48.05
42.507
22.04
0
F (N)
50.75
57.4
48.8
25.95
0
The surface area of airfoil A is (length*width*2)= 0.194 sq. Meters
The surface area of airfoil B is (length * width *2)= 0.210 sq. Meters
v=62 km/h
The dynamic pressure = 1 * p*v²
p: density of air in kilograms per cubic metre (1.225Kg/m^3), v: velocity of air in meters per
second
1- Fill out the following table (Show your calculations)
Angle of
attack
Lift
coefficient
(Airfoil 1)
Lift
coefficient
(Airfoil 2)
2- Plot the lift Coefficient vs Angle for both airfoils, and discuss your findings.
3- Determine the stall angle of both airfoils.
4- Explain how the planes fly.
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