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# D:/Basile/VisualCppProjects/hydroMEX3/hydroMEX3/hydro_source/aero_coeff_control.cpp

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    00001
    00009 #include "math.h"
    00010 #include "mex.h"
    00011 #include "string.h"
    00012
    00013 #include "Datas.h"
    00014 #include "aero_coeff_control.h"
    00015
    00016
    00017 #ifndef PI_DEF
    00018 #define pi 3.141592653589793
    00019 #define PI 3.141592653589793
    00020 #endif
    00021
    00022
    00023 void aero_coeff_control(datas *d)
    00024 {
    00025         d->Chord_right = d->Chord_max - (d->Chord_max - d->Chord_min)*(d->EE_right/d->E_foils);
    00026         d->Chord_left = d->Chord_max - (d->Chord_max - d->Chord_min)*(d->EE_left/d->E_foils);
    00027
    00028         d->A_left = 0.5*(d->Chord_left + d->Chord_min)*(d->E_foils - d->EE_left);
    00029         d->A_right = 0.5*(d->Chord_right + d->Chord_min)*(d->E_foils - d->EE_right);
    00030         d->A_yaw = d->Chord*(d->E_yaw - d->EE_yaw);
    00031
    00032         d->AR_left = (pow(d->E_foils-d->EE_left,2))/d->A_left;
    00033         d->AR_right = (pow(d->E_foils-d->EE_right,2))/d->A_right;
    00034
    00035         d->AR_yaw = d->A_yaw/pow(d->Chord,2);
    00036         d->AR_pitch = d->A_pitch/pow(d->Chord,2);
    00037
    00038         d->AR_sail = 4.4;
    00039
    00040 //%Lift reduction due to AR is supposed polynomial, degree gamma
    00041
    00042         d->gamma = 1;
    00043
    00044
    00045         d->CL_left = (1 - pow((d->EE_left/d->E_foils),d->gamma))*6.3802*d->Tan_AoA_left;
    00046         d->CD_left = 0.00485054892829 + 0.09060697805806*pow(d->Tan_AoA_left,2) + 0.5*pow(d->CL_left,2)/(pi*d->AR_left);
    00047
    00048         d->CL_right = (1 - pow(d->EE_right/d->E_foils,d->gamma))*6.3802*d->Tan_AoA_right;
    00049         d->CD_right = 0.00485054892829 + 0.09060697805806*pow(d->Tan_AoA_right,2) + 0.5*pow(d->CL_right,2)/(pi*d->AR_right);
    00050
    00051         d->CL_yaw = 6.3802*d->Tan_AoA_yaw;
    00052         d->CD_yaw = 0.00485054892829 + 0.09060697805806*pow(d->Tan_AoA_yaw,2) + 0.5*pow(d->CL_yaw,2)/(pi*d->AR_yaw);
    00053
    00054         d->CL_pitch = 6.3802*d->Tan_AoA_pitch;
    00055         d->CD_pitch = 0.00485054892829 + 0.09060697805806*pow(d->Tan_AoA_pitch,2) + pow(d->CL_pitch,2)/(pi*d->AR_pitch);
    00056
    00057 //%CL_sail = 2*Tan_AoA_sail;//%tanCal_sail;
    00058 //%CD_sail = 0.009 + 0.02*Tan_AoA_sail + 0.26*Tan_AoA_sail^2;//% + CL_sail^2/(pi*AR_sail);
    00059
    00060         d->CL_sail = 1*d->Tan_AoA_sail;//%tanCal_sail;
    00061         d->CD_sail = 0.0044 + 0.0102*d->Tan_AoA_sail + 0.1285*pow(d->Tan_AoA_sail,2);//% + CL_sail^2/(pi*AR_sail);
    00062 }