From 5b00b1e7af01b0168a8960c214e480df98a0e501 Mon Sep 17 00:00:00 2001 From: Ruben Di Battista <ruben.dibattista@skywarder.eu> Date: Sun, 19 Apr 2015 20:22:44 +0200 Subject: [PATCH] Update with better details on the Matlab file --- README.md | 45 +++++++++++++++++++++++++++++++++++++++++++++ 1 file changed, 45 insertions(+) diff --git a/README.md b/README.md index 5a2e9b1..94ff639 100644 --- a/README.md +++ b/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] + +``` -- GitLab