plz help me......! The surface of many airfoils can be described with an equatio

Question

plz help me......!

The surface of many airfoils can be described with an equation of the form y = minus plus tc/0.2 {a_0 squareroot x/c + a_1(x/c) + a_2(x/c)^2 + a_3(x/C)^3 + a_4(x/c)^4] where t is the maximum thickness as a fraction of the chord length c (e.g., t_max = ct). Given that c = 1 m and t = 0.2 m, the following values for y have been measured for a particular airfoil: Determine the constants a_0, a_1 a_2, a_3, and a_4. (Write a system of five equations and five unknowns, and use MATLAB to solve the equations.)

Explanation / Answer

%start the   script

Clc

C=1;

T=0.2;

Y= [0.08909 0.09914 0.08823 0.06107 0.03421];

X= [0.15 0.35 0.5 0.7 0.85];

For I =1:1:5;

J=1;

A (I, j) =sqrt ((x (I))/c);

J=j+1;

A (I, j) =(x (I))/c;

J=j+1;

A (I, j) = ((x (i))/c) ^2;

J=j+1;

A (I, j) = ((x (i))/c) ^3;

J=j+1;

A (I, j) = ((x (I))/c) ^4;

End

A

X=Inv (A)*transpose(y);

For k=0:1:4

Fprintf(‘a% d=%3.3f ’,k ,x(k+1))

End

Mat lab output

A=

0.3873    0.1500   0.0225   0.0034   0.0005

0.5916    0.3500   0.1225   0.0429   0.0150

0.7071    0.5000   0.2500   0.1250   0.0625

0.8367    0.7000   0.4900   0.3430   0.2401

0.990      0.8500   0.7225   0.6141   0.5220

A0=0.297

A1=-0.126

A2=-0.353

A3=0.286

A4=-0.103

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