P22) The surface of many airfoils can be described with an equation of the form Thickness max y = = a√/x/c+a₁(x/c) + 0.2 + a₂(x/c)²+az(x/c)³ + a₂(x/c)4] 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 0.35 0.5 0.7 0.85 y (m) 0.08909 0.09914 0.08823 0.06107 0.03421 Determine the constants a, a, a, a3, and a4. (Write a system of five equa- tions and five unknowns, and use MATLAB to solve the equations.) y
P22) The surface of many airfoils can be described with an equation of the form Thickness max y = = a√/x/c+a₁(x/c) + 0.2 + a₂(x/c)²+az(x/c)³ + a₂(x/c)4] 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 0.35 0.5 0.7 0.85 y (m) 0.08909 0.09914 0.08823 0.06107 0.03421 Determine the constants a, a, a, a3, and a4. (Write a system of five equa- tions and five unknowns, and use MATLAB to solve the equations.) y
Advanced Engineering Mathematics
10th Edition
ISBN:9780470458365
Author:Erwin Kreyszig
Publisher:Erwin Kreyszig
Chapter2: Second-order Linear Odes
Section: Chapter Questions
Problem 1RQ
Related questions
Question
![P22)
The surface of many airfoils can be
described with an equation of the form
Thickness
max
y = = 12₂ [a₁ √x/c+a₁(x/c)+
+ a₂(x/c)² + a₂(x/c)³ + a₂(x/c)¹]
where is the maximum thickness as a fraction of the chord length c (e.g.,
Imax= 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
0.35
0.5
0.7
0.85
y (m)
0.08909
0.09914 0.08823 0.06107 0.03421
Determine the constants a, a, a, a3, and a4. (Write a system of five equa-
tions and five unknowns, and use MATLAB to solve the equations.)
y₁](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F62576fd5-f86f-465f-ab1e-fa17d591f013%2Fe15f4d00-b212-4369-b110-eba0b2be85a1%2Fme3urxf_processed.png&w=3840&q=75)
Transcribed Image Text:P22)
The surface of many airfoils can be
described with an equation of the form
Thickness
max
y = = 12₂ [a₁ √x/c+a₁(x/c)+
+ a₂(x/c)² + a₂(x/c)³ + a₂(x/c)¹]
where is the maximum thickness as a fraction of the chord length c (e.g.,
Imax= 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
0.35
0.5
0.7
0.85
y (m)
0.08909
0.09914 0.08823 0.06107 0.03421
Determine the constants a, a, a, a3, and a4. (Write a system of five equa-
tions and five unknowns, and use MATLAB to solve the equations.)
y₁
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