\n");
print("\n\n");
//***** METRICS **********************************
print(" \n");
printf(" AC_WINGAREA %2.2f\n", $ac_wingarea);
printf(" AC_WINGSPAN %2.2f\n", $ac_wingspan);
printf(" AC_CHORD %2.2f\n", $ac_wingchord);
printf(" AC_HTAILAREA %2.2f\n", $ac_htailarea);
printf(" AC_HTAILARM %2.2f\n", $ac_htailarm);
printf(" AC_VTAILAREA %2.2f\n", $ac_vtailarea);
printf(" AC_LV %2.2f\n", $ac_vtailarm);
printf(" AC_IXX %1.0f\n", $ac_ixx);
printf(" AC_IYY %1.0f\n", $ac_iyy);
printf(" AC_IZZ %1.0f\n", $ac_izz);
printf(" AC_IXZ %1.0f\n", $ac_ixz);
printf(" AC_EMPTYWT %1.0f\n", $ac_emptyweight);
printf(" AC_CGLOC %2.1f %2.1f %2.1f\n", $ac_cglocx, $ac_cglocy, $ac_cglocz);
printf(" AC_AERORP %2.1f %2.1f %2.1f\n", $ac_aerorpx, $ac_aerorpy, $ac_aerorpz);
printf(" AC_EYEPTLOC %2.1f %2.1f %2.1f\n", $ac_eyeptlocx, $ac_eyeptlocy, $ac_eyeptlocz);
print( " AC_VRP 0 0 0\n");
print(" \n");
//***** LANDING GEAR ******************************
print(" \n");
if($ac_type == 0) { // if this is a glider
print(" AC_GEAR LEFT_MLG $ac_gearlocx_main -$ac_gearlocy_main $ac_gearlocz_main ");
print("$ac_gearspring_main $ac_geardamp_main $ac_geardynamic $ac_gearstatic ");
print("$ac_gearrolling $ac_gearsteerable_main NONE 0 $ac_retract\n");
print(" AC_GEAR RIGHT_MLG $ac_gearlocx_main $ac_gearlocy_main $ac_gearlocz_main ");
print("$ac_gearspring_main $ac_geardamp_main $ac_geardynamic $ac_gearstatic ");
print("$ac_gearrolling $ac_gearsteerable_main NONE 0 $ac_retract\n");
print(" AC_GEAR NOSE_LG $ac_gearlocx_nose $ac_gearlocy_nose $ac_gearlocz_nose ");
print("$ac_gearspring_nose $ac_geardamp_nose $ac_geardynamic $ac_gearstatic ");
print("$ac_gearrolling $ac_gearsteerable_nose NONE $ac_gearmaxsteer $ac_retract\n");
print(" AC_GEAR LEFT_WING $ac_cglocx -$ac_halfspan $ac_cglocz ");
print("$ac_gearspring_nose $ac_geardamp_nose $ac_geardynamic $ac_gearstatic ");
print("$ac_gearrolling $ac_gearsteerable_main NONE 0 $ac_retract\n");
print(" AC_GEAR RIGHT_WING $ac_cglocx -$ac_halfspan $ac_cglocz ");
print("$ac_gearspring_nose $ac_geardamp_nose $ac_geardynamic $ac_gearstatic ");
print("$ac_gearrolling $ac_gearsteerable_main NONE 0 $ac_retract\n");
}
else {
if ($ac_geartype == 0) { // if this is a tricycle gear
printf(" AC_GEAR NOSE_LG %2.1f %2.1f %2.1f", $ac_gearlocx_nose, $ac_gearlocy_nose, $ac_gearlocz_nose);
printf(" %2.1f %2.1f %2.1f %2.1f", $ac_gearspring_nose, $ac_geardamp_nose, $ac_geardynamic, $ac_gearstatic);
printf(" %2.2f $ac_gearsteerable_nose NONE %2.1f $ac_retract\n", $ac_gearrolling, $ac_gearmaxsteer);
}
printf(" AC_GEAR LEFT_MLG %2.1f %2.1f %2.1f", $ac_gearlocx_main, -$ac_gearlocy_main, $ac_gearlocz_main);
printf(" %2.1f %2.1f %2.1f %2.1f", $ac_gearspring_main, $ac_geardamp_main, $ac_geardynamic, $ac_gearstatic);
printf(" %2.2f $ac_gearsteerable_main LEFT 0 $ac_retract\n", $ac_gearrolling);
printf(" AC_GEAR RIGHT_MLG %2.1f %2.1f %2.1f", $ac_gearlocx_main, $ac_gearlocy_main, $ac_gearlocz_main);
printf(" %2.1f %2.1f %2.1f %2.1f", $ac_gearspring_main, $ac_geardamp_main, $ac_geardynamic, $ac_gearstatic);
printf(" %2.2f $ac_gearsteerable_main RIGHT 0 $ac_retract\n", $ac_gearrolling);
if ($ac_geartype == 1) { // if this is a taildragger
printf(" AC_GEAR TAIL_LG %2.1f %2.1f %2.1f", $ac_gearlocx_tail, $ac_gearlocy_tail, $ac_gearlocz_tail);
printf(" %2.1f %2.1f %2.1f %2.1f", $ac_gearspring_tail, $ac_geardamp_tail, $ac_geardynamic, $ac_gearstatic);
printf(" %2.2f $ac_gearsteerable_tail NONE 0 $ac_retract\n", $ac_gearrolling);
}
}
print(" \n");
//***** PROPULSION ***************************************
print(" \n");
if($ac_type == 0) { // if glider, do nothing here
}
else {
for($i=0; $i<$ac_numengines; $i++) {
print(" \n");
print(" XLOC $ac_englocx[$i]\n");
print(" YLOC $ac_englocy[$i]\n");
print(" ZLOC $ac_englocz[$i]\n");
print(" PITCH $ac_engpitch[$i]\n");
print(" YAW $ac_engyaw[$i]\n");
print(" FEED $ac_engfeed[$i]\n");
if($ac_enginetype == 0) {
print(" \n");
}
else {
print(" \n");
}
print(" XLOC $ac_thrusterlocx[$i]\n");
print(" YLOC $ac_thrusterlocy[$i]\n");
print(" ZLOC $ac_thrusterlocz[$i]\n");
print(" PITCH $ac_thrusterpitch[$i]\n");
print(" YAW $ac_thrusteryaw[$i]\n");
print(" \n");
print(" \n");
}
//***** FUEL TANKS **************************************
for($i=0; $i<($ac_numengines + 1); $i++) {
print(" \n");
print(" XLOC $ac_tanklocx \n");
print(" YLOC $ac_tanklocy \n");
print(" ZLOC $ac_tanklocz \n");
print(" RADIUS $ac_tankradius \n");
printf(" CAPACITY %5.1f\n", $ac_tankcapacity);
printf(" CONTENTS %5.1f\n", $ac_tankcontents);
print(" \n");
}
}
print(" \n");
//***** FLIGHT CONTROL SYSTEM ***************************
print(" \n");
print(" \n");
print(" INPUT fcs/elevator-cmd-norm\n");
print(" INPUT fcs/pitch-trim-cmd-norm\n");
print(" CLIPTO -1 1\n");
print(" \n");
print(" \n");
print(" INPUT fcs/pitch-trim-sum\n");
print(" MIN -0.350\n");
print(" MAX 0.300\n");
print(" OUTPUT fcs/elevator-pos-rad\n");
print(" \n");
print(" \n");
print(" INPUT fcs/aileron-cmd-norm\n");
print(" INPUT fcs/roll-trim-cmd-norm\n");
print(" CLIPTO -1 1\n");
print(" \n");
print(" \n");
print(" INPUT fcs/roll-trim-sum\n");
print(" MIN -0.35\n");
print(" MAX 0.35\n");
print(" OUTPUT fcs/left-aileron-pos-rad\n");
print(" \n");
print(" \n");
print(" INPUT -fcs/roll-trim-sum\n");
print(" MIN -0.35\n");
print(" MAX 0.35\n");
print(" OUTPUT fcs/right-aileron-pos-rad\n");
print(" \n");
print(" \n");
print(" INPUT fcs/rudder-cmd-norm\n");
print(" INPUT fcs/yaw-trim-cmd-norm\n");
print(" CLIPTO -1 1\n");
print(" \n");
if($ac_yawdamper == 1) {
print(" \n");
print(" INPUT velocities/r-aero-rad_sec\n");
print(" SCHEDULED_BY aero/qbar-psf\n");
print(" ROWS 2\n");
print(" 3.00 0.00\n");
print(" 11.00 2.00\n");
print(" \n");
print(" \n");
print(" INPUT aero/beta-rad\n");
print(" SCHEDULED_BY aero/qbar-psf\n");
print(" ROWS 2\n");
print(" 3.00 0.00\n");
print(" 11.00 0.00\n");
print(" \n");
print(" \n");
print(" INPUT fcs/yaw-damper-beta\n");
print(" INPUT fcs/yaw-damper-rate\n");
print(" CLIPTO -0.2 0.2\n");
print(" \n");
print(" \n");
print(" INPUT fcs/yaw-damper-sum\n");
print(" SCHEDULED_BY aero/qbar-psf\n");
print(" ROWS 2\n");
print(" 2.99 0.0\n");
print(" 3.00 1.0\n");
print(" \n");
print(" \n");
print(" INPUT fcs/rudder-command-sum\n");
print(" INPUT fcs/yaw-damper-final\n");
print(" CLIPTO -1 1\n");
print(" \n");
print(" \n");
print(" INPUT fcs/rudder-sum\n");
print(" MIN -0.35\n");
print(" MAX 0.35\n");
print(" OUTPUT fcs/rudder-pos-rad\n");
print(" \n");
}
else {
print(" \n");
print(" INPUT fcs/rudder-command-sum\n");
print(" MIN -0.35\n");
print(" MAX 0.35\n");
print(" OUTPUT fcs/rudder-pos-rad\n");
print(" \n");
}
print(" \n");
print(" INPUT fcs/flap-cmd-norm\n");
print(" DETENTS 3\n");
print(" 0 0\n");
print(" 15 4\n");
print(" 30 3\n");
print(" OUTPUT fcs/flap-pos-deg\n");
print(" \n");
if($ac_gearretract == 1) {
print(" \n");
print(" INPUT gear/gear-cmd-norm\n");
print(" DETENTS 2\n");
print(" 0 0\n");
print(" 1 5\n");
print(" OUTPUT gear/gear-pos-norm\n");
print(" \n");
}
print(" \n");
print(" INPUT fcs/speedbrake-cmd-norm\n");
print(" DETENTS 2\n");
print(" 0 0\n");
print(" 1 1\n");
print(" OUTPUT fcs/speedbrake-pos-norm\n");
print(" \n");
print(" \n");
//***** AERODYNAMICS ******************************************
print(" \n");
// build a lift curve with four points
print(" \n");
print(" \n");
print(" Lift_due_to_alpha\n");
print(" 4\n");
print(" aero/alpha-rad\n");
print(" aero/qbar-psf|metrics/Sw-sqft\n");
$point = -($ac_CLalpha * 0.2) + $ac_CL0;
printf(" -0.20 %4.3f\n", $point);
printf(" 0.00 %4.3f\n", $ac_CL0);
$alpha = ($ac_CLmax - $ac_CL0) / $ac_CLalpha;
printf(" %3.2f %4.3f\n", $alpha, $ac_CLmax);
$point = $ac_CLmax - (0.6 * $alpha * $ac_CLalpha);
printf(" 0.60 %4.3f\n", $point);
print(" \n");
print(" \n");
print(" Delta_Lift_due_to_flaps\n");
print(" aero/qbar-psf|metrics/Sw-sqft|fcs/flap-pos-norm\n");
print(" $ac_dCLflaps\n");
print(" \n");
print(" \n");
print(" Delta_Lift_due_to_speedbrake\n");
print(" aero/qbar-psf|metrics/Sw-sqft|fcs/speedbrake-pos-norm\n");
print(" $ac_dCLspeedbrake\n");
print(" \n");
print(" \n");
print(" Lift_due_to_Elevator_Deflection\n");
print(" aero/qbar-psf|metrics/Sw-sqft|fcs/elevator-pos-rad\n");
print(" $ac_CLde\n");
print(" \n");
print(" \n");
//***** DRAG ******************************************************
print(" \n");
print(" \n");
print(" Drag_at_zero_lift\n");
print(" 5\n");
print(" aero/alpha-rad\n");
print(" aero/qbar-psf|metrics/Sw-sqft\n");
print(" -1.57 1.500\n");
$ac_CD02 = $ac_CD0 * 2;
printf(" -0.26 %4.3f\n", $ac_CD02);
printf(" 0.00 %4.3f\n", $ac_CD0);
printf(" 0.26 %4.3f\n", $ac_CD02);
print(" 1.57 1.500\n");
print(" \n");
print(" \n");
print(" Induced_drag\n");
print(" aero/qbar-psf|metrics/Sw-sqft|aero/cl-squared-norm\n");
print(" $ac_K\n");
print(" \n");
print(" \n");
print(" Drag_due_to_mach\n");
print(" 4\n");
print(" velocities/mach-norm\n");
print(" aero/qbar-psf|metrics/Sw-sqft\n");
print(" 0.0 0.000\n");
print(" $ac_Mcrit 0.000\n");
print(" 1.1 0.023\n");
print(" 1.8 0.015\n");
print(" \n");
print(" \n");
print(" Drag_due_to_flaps\n");
print(" aero/qbar-psf|metrics/Sw-sqft|fcs/flap-pos-norm\n");
print(" $ac_CDflaps\n");
print(" \n");
if($ac_gearretract == 1) {
print(" \n");
print(" Drag_due_to_gear\n");
print(" aero/qbar-psf|metrics/Sw-sqft|gear/gear-pos-norm\n");
print(" $ac_CDgear\n");
print(" \n");
}
print(" \n");
print(" Drag_due_to_speedbrakes\n");
print(" aero/qbar-psf|metrics/Sw-sqft|fcs/speedbrake-pos-norm\n");
print(" $ac_CDspeedbrake\n");
print(" \n");
print(" \n");
print(" Drag_due_to_sideslip\n");
print(" 5\n");
print(" aero/beta-rad\n");
print(" aero/qbar-psf|metrics/Sw-sqft\n");
print(" -1.57 1.230\n");
$ac_CDb26 = $ac_CDbeta * 0.25; // CD at beta of 0.26 radians
printf(" -0.26 %4.3f\n", $ac_CDb26);
printf(" 0.00 0.00\n");
printf(" 0.26 %4.3f\n", $ac_CDb26);
print(" 1.57 1.230\n");
print(" \n");
print(" \n");
print(" Drag_due_to_Elevator_Deflection\n");
print(" aero/qbar-psf|metrics/Sw-sqft|fcs/elevator-pos-norm\n");
print(" $ac_CDflaps\n");
print(" \n");
print(" \n");
//***** SIDE *************************************************
print(" \n");
print(" \n");
print(" Side_force_due_to_beta\n");
print(" aero/qbar-psf|metrics/Sw-sqft|aero/beta-rad\n");
print(" $ac_CYbeta\n");
print(" \n");
print(" \n");
//***** ROLL ************************************************
print(" \n");
print(" \n");
print(" Roll_moment_due_to_beta\n");
print(" aero/qbar-psf|metrics/Sw-sqft|metrics/bw-ft|aero/beta-rad\n");
print(" $ac_Clbeta\n");
print(" \n");
print(" \n");
print(" Roll_moment_due_to_roll_rate\n");
print(" aero/qbar-psf|metrics/Sw-sqft|metrics/bw-ft|aero/bi2vel|velocities/p-aero-rad_sec\n");
print(" $ac_Clp\n");
print(" \n");
print(" \n");
print(" Roll_moment_due_to_yaw_rate\n");
print(" aero/qbar-psf|metrics/Sw-sqft|metrics/bw-ft|aero/bi2vel|velocities/r-aero-rad_sec\n");
print(" $ac_Clr\n");
print(" \n");
print(" \n");
print(" Roll_moment_due_to_aileron\n");
print(" 2\n");
print(" velocities/mach-norm\n");
print(" aero/qbar-psf|metrics/Sw-sqft|metrics/bw-ft|fcs/left-aileron-pos-rad\n");
print(" 0.0 $ac_Clda\n");
$ac_Clda3 = $ac_Clda * 0.333;
printf(" 2.0 %4.3f\n", $ac_Clda3);
print(" \n");
print(" \n");
print(" Roll_moment_due_to_rudder\n");
print(" aero/qbar-psf|metrics/Sw-sqft|metrics/bw-ft|fcs/rudder-pos-rad\n");
print(" $ac_Cldr\n");
print(" \n");
print(" \n");
//***** PITCH *****************************************
print(" \n");
print(" \n");
print(" Pitch_moment_due_to_alpha\n");
print(" aero/qbar-psf|metrics/Sw-sqft|metrics/cbarw-ft|aero/alpha-rad\n");
print(" $ac_Cmalpha\n");
print(" \n");
print(" \n");
print(" Pitch_moment_due_to_elevator\n");
print(" 2\n");
print(" velocities/mach-norm\n");
print(" aero/qbar-psf|metrics/Sw-sqft|metrics/cbarw-ft|fcs/elevator-pos-rad\n");
print(" 0.0 $ac_Cmde\n");
$ac_Cmde4 = $ac_Cmde * 0.25;
printf(" 2.0 %4.3f\n", $ac_Cmde4);
print(" \n");
print(" \n");
print(" Pitch_moment_due_to_pitch_rate\n");
print(" aero/qbar-psf|metrics/Sw-sqft|metrics/cbarw-ft|aero/ci2vel|velocities/q-aero-rad_sec\n");
print(" $ac_Cmq\n");
print(" \n");
print(" \n");
print(" Pitch_moment_due_to_alpha_rate\n");
print(" aero/qbar-psf|metrics/Sw-sqft|metrics/cbarw-ft|aero/ci2vel|aero/alphadot-rad_sec\n");
print(" $ac_Cmadot\n");
print(" \n");
print(" \n");
//***** YAW ***********************************************
print(" \n");
print(" \n");
print(" Yaw_moment_due_to_beta\n");
print(" aero/qbar-psf|metrics/Sw-sqft|metrics/bw-ft|aero/beta-rad\n");
print(" $ac_Cnbeta\n");
print(" \n");
print(" \n");
print(" Yaw_moment_due_to_yaw_rate\n");
print(" aero/qbar-psf|metrics/Sw-sqft|metrics/bw-ft|aero/bi2vel|velocities/r-aero-rad_sec\n");
print(" $ac_Cnr\n");
print(" \n");
print(" \n");
print(" Yaw_moment_due_to_rudder\n");
print(" aero/qbar-psf|metrics/Sw-sqft|metrics/bw-ft|fcs/rudder-pos-rad\n");
print(" $ac_Cndr\n");
print(" \n");
print(" \n");
print(" Adverse_yaw\n");
print(" aero/qbar-psf|metrics/Sw-sqft|metrics/bw-ft|fcs/left-aileron-pos-rad\n");
print(" $ac_Cnda\n");
print(" \n");
print(" \n");
print(" \n");
print("\n");
?>