Wind tunnel measurements of the pressure and skin friction around a NACA 2415 airfoil at 8 degrees angle of attack resulted in the following data of pressure and skin friction coefficients C_p(I) and C_f(I) at locations X(I) & Y(I) over the airfoil.

X	Y	Cp	Cf*10^3
1	0.00157	0.00122	0.5
0.9974	0.00223	0.00432	1
0.9893	0.00419	0.00876	2
0.9759	0.00739	-0.0126	3
0.95733	0.01172	-0.0165	5
0.93377	0.01705	-0.0211	5
0.90548	0.02323	-0.0313	6
0.87275	0.03006	-0.0279	6
0.83591	0.03738	-0.1911	6
0.79536	0.04498	-0.2321	6
0.75154	0.05267	-0.261	6
0.7049	0.06025	-0.3452	6
0.65595	0.06753	-0.4233	6
0.60524	0.07431	-0.5043	6
0.55331	0.0804	-0.5467	6
0.50074	0.08562	-0.7654	6
0.44811	0.08978	-0.9391	6
0.39597	0.09272	-0.9453	6
0.34448	0.09409	-1.0876	7
0.29469	0.09366	-1.2	7
0.24722	0.0914	-1.3233	8
0.20261	0.08736	-1.4203	8
0.16142	0.08163	-1.7688	8
0.12411	0.07438	-1.8716	9
0.09112	0.0658	-2.0511	9
0.06282	0.05615	-2.2698	9
0.03952	0.04566	-2.3861	9
0.02145	0.0346	-2.6653	9
0.00878	0.02319	-0.544	9
0.00161	0.01161	-0.3443	10
0	0	0	0
0.00387	-0.01106	0.61	15
0.01308	-0.02103	1	15
0.0275	-0.02985	0.9209	14
0.04694	-0.03748	0.8521	12
0.07115	-0.04387	0.4246	11
0.09986	-0.04899	0.2765	9
0.13275	-0.05282	0.2192	8
0.16945	-0.05539	0.1835	7
0.2096	-0.05676	0.2543	7
0.25278	-0.05703	0.24011	7
0.29857	-0.05633	0.27001	7
0.34651	-0.05483	0.29	7
0.39612	-0.05272	0.24132	8
0.44737	-0.05003	0.23888	8
0.49926	-0.04673	0.23421	8
0.55122	-0.04298	0.23234	9
0.60267	-0.03893	0.1731	9
0.65306	-0.03472	0.13002	9
0.70184	-0.03048	0.12882	8
0.74846	-0.02628	0.12799	7
0.79242	-0.02222	0.171	7
0.83322	-0.01836	0.0862	6
0.8704	-0.01477	0.061	6
0.90354	-0.01151	0.0572	6
0.93225	-0.00862	0.0473	6
0.95622	-0.00616	0.0132	5
0.97516	-0.00419	0.00931	5
0.98885	-0.00275	0.0081	5
0.99712	-0.00187	0.00061	5
1	-0.00157	0.0029	4

Calculate the lift, drag and moment coefficients. Use two different numerical approaches to compare your results.

I need the solution on how to solve this using MATLAB, if that is not possible i just need the steps/formula on how to solve it and i will try to input it in MATLAB myself