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The surface of many airfoils can be described with an equation of the form tc y = = [√x/c+ a₁ (x/c)+ + a2(x/c)² + az(x/c)³ + a₁(x/c)4] y Thickness imax where is the maximum thickness as a fraction of the chord length c (e.g., 'max = ct). Given that c = 1 m and t = 0.2 m, the following values for y have been measured for a particular airfoil: x (m) 0.15 y (m) 0.08909 0.35 0.5 0.7 0.85 0.09914 0.08823 0.06107 0.03421 Determine the constants a0, a1, a2, a3, and a4. (Write a system of five equa- tions and five unknowns and use MATLAB to solve the equations.)

The surface of many airfoils can be described with an equation of the form tc y = = [√x/c+ a₁ (x/c)+ + a2(x/c)² + az(x/c)³ + a₁(x/c)4] y Thickness imax where is the maximum thickness as a fraction of the chord length c (e.g., 'max = ct). Given that c = 1 m and t = 0.2 m, the following values for y have been measured for a particular airfoil: x (m) 0.15 y (m) 0.08909 0.35 0.5 0.7 0.85 0.09914 0.08823 0.06107 0.03421 Determine the constants a0, a1, a2, a3, and a4. (Write a system of five equa- tions and five unknowns and use MATLAB to solve the equations.)

Database System Concepts
Database System Concepts
7th Edition
ISBN:9780078022159
Author:Abraham Silberschatz Professor, Henry F. Korth, S. Sudarshan
Publisher:Abraham Silberschatz Professor, Henry F. Korth, S. Sudarshan
Chapter1: Introduction
Section: Chapter Questions
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Solve the following using Matlab

The surface of many airfoils can be described with an equation of the form tc y = = [√x/c+ a₁ (x/c)+ + a2(x/c)² + az(x/c)³ + a₁(x/c)4] y Thickness imax where is the maximum thickness as a fraction of the chord length c (e.g., 'max = ct). Given that c = 1 m and t = 0.2 m, the following values for y have been measured for a particular airfoil: x (m) 0.15 y (m) 0.08909 0.35 0.5 0.7 0.85 0.09914 0.08823 0.06107 0.03421 Determine the constants a0, a1, a2, a3, and a4. (Write a system of five equa- tions and five unknowns and use MATLAB to solve the equations.)
Transcribed Image Text:The surface of many airfoils can be described with an equation of the form tc y = = [√x/c+ a₁ (x/c)+ + a2(x/c)² + az(x/c)³ + a₁(x/c)4] y Thickness imax where is the maximum thickness as a fraction of the chord length c (e.g., 'max = ct). Given that c = 1 m and t = 0.2 m, the following values for y have been measured for a particular airfoil: x (m) 0.15 y (m) 0.08909 0.35 0.5 0.7 0.85 0.09914 0.08823 0.06107 0.03421 Determine the constants a0, a1, a2, a3, and a4. (Write a system of five equa- tions and five unknowns and use MATLAB to solve the equations.)
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