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 (lengthwidth 2)= 0.194 sq. Meters The surface area of airfoil B is (lengthwidth2)= 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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