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Using thin-airfoil theory, design an airfoil camber line that meets the following three requirements: ⚫ The lift coefficient is c₁ = 0.5 ⚫ There is no leading-edge suction peak • The airfoil has 10% static stability, SM = 10% a) Based on the requirements, determine the thin-airfoil theory constants B1 and B2. b) Assume that the camber line is given by Ze =a = a²² (1-2²) (1+6²) с Determine the constants a and b, and the angle of attack a, such that the design requirements are met. Provide a computer-generated plot of the camber line. c) Plot the difference in pressure coefficient versus x/c, Acp(x/c) = Cp,lower (x/c) - Cp,upper (x/c), and verify numerically, using point values of Acp and trapezoidal integration (trapz) that ce == 1 A(z) dz

Using thin-airfoil theory, design an airfoil camber line that meets the following three requirements: ⚫ The lift coefficient is c₁ = 0.5 ⚫ There is no leading-edge suction peak • The airfoil has 10% static stability, SM = 10% a) Based on the requirements, determine the thin-airfoil theory constants B1 and B2. b) Assume that the camber line is given by Ze =a = a²² (1-2²) (1+6²) с Determine the constants a and b, and the angle of attack a, such that the design requirements are met. Provide a computer-generated plot of the camber line. c) Plot the difference in pressure coefficient versus x/c, Acp(x/c) = Cp,lower (x/c) - Cp,upper (x/c), and verify numerically, using point values of Acp and trapezoidal integration (trapz) that ce == 1 A(z) dz

Elements Of Electromagnetics
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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Using thin-airfoil theory, design an airfoil camber line that meets the following three requirements: ⚫ The lift coefficient is c₁ = 0.5 ⚫ There is no leading-edge suction peak • The airfoil has 10% static stability, SM = 10% a) Based on the requirements, determine the thin-airfoil theory constants B1 and B2.
Transcribed Image Text:Using thin-airfoil theory, design an airfoil camber line that meets the following three requirements: ⚫ The lift coefficient is c₁ = 0.5 ⚫ There is no leading-edge suction peak • The airfoil has 10% static stability, SM = 10% a) Based on the requirements, determine the thin-airfoil theory constants B1 and B2.
b) Assume that the camber line is given by Ze =a = a²² (1-2²) (1+6²) с Determine the constants a and b, and the angle of attack a, such that the design requirements are met. Provide a computer-generated plot of the camber line. c) Plot the difference in pressure coefficient versus x/c, Acp(x/c) = Cp,lower (x/c) - Cp,upper (x/c), and verify numerically, using point values of Acp and trapezoidal integration (trapz) that ce == 1 A(z) dz
Transcribed Image Text:b) Assume that the camber line is given by Ze =a = a²² (1-2²) (1+6²) с Determine the constants a and b, and the angle of attack a, such that the design requirements are met. Provide a computer-generated plot of the camber line. c) Plot the difference in pressure coefficient versus x/c, Acp(x/c) = Cp,lower (x/c) - Cp,upper (x/c), and verify numerically, using point values of Acp and trapezoidal integration (trapz) that ce == 1 A(z) dz
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