Update with better details on the Matlab file

README.md

@@ -12,3 +12,48 @@ python datcom_parser.py filename
 ```
 
 The filename is optional. Without it the parser will look for the `for006.dat' file.
+
+## Output File ###
+The Output file is composed by two structures: `Coeffs` and `State`. 
+`Coeffs` contains all the aerodynamic coefficients interpolated over the 4 states (AoA, Mach, Altitude, Sidesplip angles) and the struct `State` contains the set of states (Aoa, Mach, Altitude, Sideslip Angle) the coefficients have been calculated on and the position of the center of gravity.
+
+```
+Coeffs = 
+
+      CAQ: [4-D double]
+     CLNP: [4-D double]
+      CMA: [4-D double]
+    CL_CD: [4-D double]
+      CMQ: [4-D double]
+     CLNB: [4-D double]
+      CYR: [4-D double]
+      CYP: [4-D double]
+     CMAD: [4-D double]
+      CNQ: [4-D double]
+      CYB: [4-D double]
+     CNAD: [4-D double]
+      CLL: [4-D double]
+      CLN: [4-D double]
+       CN: [4-D double]
+       CM: [4-D double]
+       CL: [4-D double]
+       CA: [4-D double]
+       CD: [4-D double]
+       CY: [4-D double]
+     CLNR: [4-D double]
+      CNA: [4-D double]
+     CLLB: [4-D double]
+     CLLP: [4-D double]
+     CLLR: [4-D double]
+    X_C_P: [4-D double]
+    ```
+```
+State = 
+
+      Altitudes: [3x1 double]
+         Alphas: [19x1 double]
+    Mom. Center: 1.5500
+          Betas: [5x1 double]
+          Machs: [3x1 double]
+
+```