// Updated: 11 Apr 2009, DPC - use "0|1" for gear retractability // Updated: 21 Jul 2011, DPC - fix rudder travel limit bug // Updated: 2 Nov 2011, RKJ - better fuel estimates, payload pointmass //***** GET DATA FROM USER *************************** $ac_units = $_POST['ac_units']; $ac_name = $_POST['ac_name']; $ac_type = $_POST['ac_type']; $ac_weight = $_POST['ac_weight']; $ac_wingspan = $_POST['ac_wingspan']; $ac_wingincidence = $_POST['ac_wingincidence']; $ac_length = $_POST['ac_length']; $ac_wingarea = $_POST['ac_wingarea']; $ac_geartype = $_POST['ac_geartype']; $ac_gearretract = $_POST['ac_gearretract']; $ac_numengines = $_POST['ac_numengines']; $ac_enginetype = $_POST['ac_enginetype']; $ac_enginelayout = $_POST['ac_enginelayout']; $ac_enginename = $_POST['ac_enginename']; $ac_enginepower = $_POST['ac_enginepower']; $ac_engineunits = $_POST['ac_engineunits']; $ac_augmented = $_POST['ac_augmented']; $ac_yawdamper = $_POST['ac_yawdamper']; $ac_wingchord = $_POST['ac_wingchord']; $ac_htailarea = $_POST['ac_htailarea']; $ac_htailarm = $_POST['ac_htailarm']; $ac_vtailarea = $_POST['ac_vtailarea']; $ac_vtailarm = $_POST['ac_vtailarm']; $ac_emptyweight = $_POST['ac_emptyweight']; $ac_ixx = $_POST['ac_ixx']; $ac_iyy = $_POST['ac_iyy']; $ac_izz = $_POST['ac_izz']; header("Content-type: text/plain"); header("Content-Disposition: inline; filename=\"$ac_name.xml\""); //***** CONVERT TO ENGLISH UNITS ********************* $ft_to_in = 12; $m_to_ft = 3.281; $kg_to_lbs = 2.205; if ($ac_units == 1) { $ac_weight *= $kg_to_lbs; $ac_wingspan *= $m_to_ft; $ac_length *= $m_to_ft; $ac_wingarea *= $m_to_ft * $m_to_ft; $ac_wingchord *= $m_to_ft; $ac_htailarea *= $m_to_ft * $m_to_ft; $ac_htailarm *= $m_to_ft; $ac_vtailarea *= $m_to_ft * $m_to_ft; $ac_vtailarm *= $m_to_ft; $ac_emptyweight *= $kg_to_lbs; } //***** METRICS *************************************** // first, estimate wing loading in psf switch($ac_type) { case 0: $ac_wingloading = 7.0; break; // glider case 1: $ac_wingloading = 14.0; break; // light single case 2: $ac_wingloading = 29.0; break; // light twin case 3: $ac_wingloading = 45.0; break; // WW2 fighter, racer case 4: $ac_wingloading = 95.0; break; // single-eng jet fighter case 5: $ac_wingloading = 100.0; break; // 2-eng jet fighter case 6: $ac_wingloading = 110.0; break; // 2-eng jet transport case 7: $ac_wingloading = 110.0; break; // 3-eng jet transport case 8: $ac_wingloading = 110.0; break; // 4-eng jet transport case 9: $ac_wingloading = 57.0; break; // prop transport } // if no wing area given, use wing loading to estimate if ($ac_wingarea == 0) { $wingarea_input = false; $ac_wingarea = $ac_weight / $ac_wingloading; } else { $wingarea_input = true; $ac_wingloading = $ac_weight / $ac_wingarea; } // calculate wing chord $ac_wingchord = $ac_wingarea / $ac_wingspan; // calculate aspect ratio $ac_aspectratio = $ac_wingspan / $ac_wingchord; // calculate half-span $ac_halfspan = $ac_wingspan / 2; // for now let's use a standard 2 degrees wing incidence if($ac_wingincidence == 0) { $ac_wingincidence = 2.0; } // estimate horizontal tail area if ($ac_htailarea == 0) { switch($ac_type) { case 0: $ac_htailarea = $ac_wingarea * 0.12; break; case 1: $ac_htailarea = $ac_wingarea * 0.16; break; case 2: $ac_htailarea = $ac_wingarea * 0.16; break; case 3: $ac_htailarea = $ac_wingarea * 0.17; break; case 4: $ac_htailarea = $ac_wingarea * 0.20; break; case 5: $ac_htailarea = $ac_wingarea * 0.20; break; case 6: $ac_htailarea = $ac_wingarea * 0.25; break; case 7: $ac_htailarea = $ac_wingarea * 0.25; break; case 8: $ac_htailarea = $ac_wingarea * 0.25; break; case 9: $ac_htailarea = $ac_wingarea * 0.16; break; } } // estimate distance from CG to horizontal tail aero center if ($ac_htailarm == 0) { switch($ac_type) { case 0: $ac_htailarm = $ac_length * 0.60; break; case 1: $ac_htailarm = $ac_length * 0.52; break; case 2: $ac_htailarm = $ac_length * 0.50; break; case 3: $ac_htailarm = $ac_length * 0.60; break; case 4: $ac_htailarm = $ac_length * 0.40; break; case 5: $ac_htailarm = $ac_length * 0.40; break; case 6: $ac_htailarm = $ac_length * 0.45; break; case 7: $ac_htailarm = $ac_length * 0.45; break; case 8: $ac_htailarm = $ac_length * 0.45; break; case 9: $ac_htailarm = $ac_length * 0.50; break; } } // estimate vertical tail area if ($ac_vtailarea == 0) { switch($ac_type) { case 0: $ac_vtailarea = $ac_wingarea * 0.10; break; case 1: $ac_vtailarea = $ac_wingarea * 0.10; break; case 2: $ac_vtailarea = $ac_wingarea * 0.18; break; case 3: $ac_vtailarea = $ac_wingarea * 0.10; break; case 4: $ac_vtailarea = $ac_wingarea * 0.12; break; case 5: $ac_vtailarea = $ac_wingarea * 0.18; break; case 6: $ac_vtailarea = $ac_wingarea * 0.20; break; case 7: $ac_vtailarea = $ac_wingarea * 0.20; break; case 8: $ac_vtailarea = $ac_wingarea * 0.20; break; case 9: $ac_vtailarea = $ac_wingarea * 0.18; break; } } // estimate distance from CG to vertical tail aero center if ($ac_vtailarm == 0) { switch($ac_type) { case 0: $ac_vtailarm = $ac_length * 0.60; break; case 1: $ac_vtailarm = $ac_length * 0.50; break; case 2: $ac_vtailarm = $ac_length * 0.50; break; case 3: $ac_vtailarm = $ac_length * 0.60; break; case 4: $ac_vtailarm = $ac_length * 0.40; break; case 5: $ac_vtailarm = $ac_length * 0.40; break; case 6: $ac_vtailarm = $ac_length * 0.45; break; case 7: $ac_vtailarm = $ac_length * 0.45; break; case 8: $ac_vtailarm = $ac_length * 0.45; break; case 9: $ac_vtailarm = $ac_length * 0.50; break; } } //***** EMPTY WEIGHT ********************************* // estimate empty weight, based on max weight if ($ac_emptyweight == 0) { switch($ac_type) { case 0: $ac_emptyweight = $ac_weight * .84; case 1: $ac_emptyweight = $ac_weight * .62; case 2: $ac_emptyweight = $ac_weight * .61; case 3: $ac_emptyweight = $ac_weight * .61; case 4: $ac_emptyweight = $ac_weight * .53; case 5: $ac_emptyweight = $ac_weight * .50; case 6: $ac_emptyweight = $ac_weight * .55; case 7: $ac_emptyweight = $ac_weight * .52; case 8: $ac_emptyweight = $ac_weight * .49; case 9: $ac_emptyweight = $ac_weight * .60; } } //***** MOMENTS OF INERTIA ****************************** if(($ac_ixx == 0) && ($ac_iyy == 0) && ($ac_izz == 0)) { // use Roskam's formulae to estimate moments of inertia switch($ac_type) { // moment-of-inertia factors case 0: $Rx = 0.34;$Ry = 0.33;$Rz = 0.47; break; case 1: $Rx = 0.27;$Ry = 0.36;$Rz = 0.42; break; case 2: $Rx = 0.27;$Ry = 0.35;$Rz = 0.45; break; case 3: $Rx = 0.27;$Ry = 0.36;$Rz = 0.42; break; case 4: $Rx = 0.27;$Ry = 0.35;$Rz = 0.40; break; case 5: $Rx = 0.29;$Ry = 0.34;$Rz = 0.41; break; case 6: $Rx = 0.25;$Ry = 0.38;$Rz = 0.46; break; case 7: $Rx = 0.25;$Ry = 0.36;$Rz = 0.47; break; case 8: $Rx = 0.32;$Ry = 0.34;$Rz = 0.47; break; case 9: $Rx = 0.32;$Ry = 0.35;$Rz = 0.47; break; } // These are for an empty airplane $ac_rawixx = ($ac_emptyweight / 32.2)* pow(($Rx * $ac_wingspan / 2), 2); $ac_rawiyy = ($ac_emptyweight / 32.2)* pow(($Ry * $ac_length / 2), 2); $ac_rawizz = ($ac_emptyweight / 32.2)* pow(($Rz * (($ac_wingspan + $ac_length)/2) / 2), 2); // assume 4 degree angle between longitudinal and inertial axes // $ac_rawixz = abs($ac_rawizz - $ac_rawixx) * 0.06975647; $ac_ixx = $ac_rawixx; $ac_iyy = $ac_rawiyy; $ac_izz = $ac_rawizz; } $ac_ixz = 0; $ac_iyz = 0; $ac_ixy = 0; //***** CG LOCATION *********************************** $ac_cglocx = ($ac_length - $ac_htailarm) * $ft_to_in; $ac_cglocy = 0; $ac_cglocz = -($ac_length / 40.0) * $ft_to_in; //***** AERO REFERENCE POINT ************************** $ac_aerorpx = $ac_cglocx; $ac_aerorpy = 0; $ac_aerorpz = 0; //***** PILOT EYEPOINT ********************************* // place pilot's eyepoint based on airplane type switch($ac_type) { case 0: $ac_eyeptlocx = ($ac_length * 0.19) * $ft_to_in; break; case 1: $ac_eyeptlocx = ($ac_length * 0.13) * $ft_to_in; break; case 2: $ac_eyeptlocx = ($ac_length * 0.17) * $ft_to_in; break; case 3: $ac_eyeptlocx = ($ac_length * 0.28) * $ft_to_in; break; case 4: $ac_eyeptlocx = ($ac_length * 0.20) * $ft_to_in; break; case 5: $ac_eyeptlocx = ($ac_length * 0.20) * $ft_to_in; break; case 6: $ac_eyeptlocx = ($ac_length * 0.07) * $ft_to_in; break; case 7: $ac_eyeptlocx = ($ac_length * 0.07) * $ft_to_in; break; case 8: $ac_eyeptlocx = ($ac_length * 0.07) * $ft_to_in; break; case 9: $ac_eyeptlocx = ($ac_length * 0.08) * $ft_to_in; break; } switch($ac_type) { case 0: $ac_eyeptlocy = 0; break; case 1: $ac_eyeptlocy = -18; break; case 2: $ac_eyeptlocy = -18; break; case 3: $ac_eyeptlocy = 0; break; case 4: $ac_eyeptlocy = 0; break; case 5: $ac_eyeptlocy = 0; break; case 6: $ac_eyeptlocy = -30; break; case 7: $ac_eyeptlocy = -30; break; case 8: $ac_eyeptlocy = -32; break; case 9: $ac_eyeptlocy = -24; break; } switch($ac_type) { case 0: $ac_eyeptlocz = 9; break; case 1: $ac_eyeptlocz = 45; break; case 2: $ac_eyeptlocz = 45; break; case 3: $ac_eyeptlocz = 40; break; case 4: $ac_eyeptlocz = 36; break; case 5: $ac_eyeptlocz = 38; break; case 6: $ac_eyeptlocz = 70; break; case 7: $ac_eyeptlocz = 75; break; case 8: $ac_eyeptlocz = 80; break; case 9: $ac_eyeptlocz = 65; break; } //***** LANDING GEAR ********************************* // set main gear longitudinal location relative to CG switch($ac_geartype) { case 0: $ac_gearlocx_main = $ac_cglocx * 1.04; break; case 1: $ac_gearlocx_main = $ac_cglocx * 0.91; break; } // set main gear lateral location switch($ac_type) { case 0: $ac_gearlocy_main = $ac_wingspan * 0.005 * $ft_to_in; break; case 1: $ac_gearlocy_main = $ac_wingspan * 0.09 * $ft_to_in; break; case 2: $ac_gearlocy_main = $ac_wingspan * 0.09 * $ft_to_in; break; case 3: $ac_gearlocy_main = $ac_wingspan * 0.15 * $ft_to_in; break; case 4: $ac_gearlocy_main = $ac_wingspan * 0.09 * $ft_to_in; break; case 5: $ac_gearlocy_main = $ac_wingspan * 0.09 * $ft_to_in; break; case 6: $ac_gearlocy_main = $ac_wingspan * 0.09 * $ft_to_in; break; case 7: $ac_gearlocy_main = $ac_wingspan * 0.09 * $ft_to_in; break; case 8: $ac_gearlocy_main = $ac_wingspan * 0.09 * $ft_to_in; break; case 9: $ac_gearlocy_main = $ac_wingspan * 0.11 * $ft_to_in; break; } // set main gear length (from aircraft centerline, extended) switch($ac_geartype) { case 0: $ac_gearlocz_main = -($ac_length * 0.12 * $ft_to_in); break; case 1: $ac_gearlocz_main = -($ac_length * 0.20 * $ft_to_in); break; } if($ac_type == 0) $ac_gearlocz_main = -($ac_length / 10 * $ft_to_in); // glider $ac_gearlocx_nose = $ac_length * 0.13 * $ft_to_in; $ac_gearlocy_nose = 0; $ac_gearlocz_nose = $ac_gearlocz_main; if($ac_type == 0) $ac_gearlocz_nose = $ac_gearlocz_main * 0.6; // glider $ac_gearlocx_tail = $ac_length * 0.91 * $ft_to_in; $ac_gearlocy_tail = 0; $ac_gearlocz_tail = $ac_gearlocz_main * 0.30; $ac_gearspring_main = $ac_weight * 1.0; $ac_gearspring_nose = $ac_weight * 0.3; $ac_gearspring_tail = $ac_weight * 1.0; $ac_geardamp_main = $ac_weight * 0.5; $ac_geardamp_nose = $ac_weight * 0.15; $ac_geardamp_tail = $ac_weight * 0.5; $ac_geardynamic = 0.5; $ac_gearstatic = 0.8; $ac_bearingstatic = 0.006; // 2 x 2 x 0.0015, friction for a ball-bearing $ac_gearrolling = 0.02; $ac_bearingrolling = 0.003; // 2 x 0.0015, friction for a ball-bearing if($ac_type == 0) $ac_gearrolling = 0.5; // glider $ac_gearsteerable_nose = 'STEERABLE'; $ac_gearsteerable_main = 'FIXED'; $ac_gearsteerable_tail = 'CASTERED'; $ac_gearmaxsteer = 5; if($ac_gearretract == 0) $ac_retract = '0'; else $ac_retract = '1'; //***** PROPULSION ************************************ // spread engines out in reasonable locations // forward fuselage engines if ($ac_enginelayout == 0) { $leftmost = ($ac_numengines * -20) + 20; for( $i=0; $i<$ac_numengines; $i++) { $ac_englocx[$i] = 36.0; $ac_englocy[$i] = $leftmost + ($i * 40); $ac_englocz[$i] = 0; } } // mid fuselage engines if ($ac_enginelayout == 1) { $leftmost = ($ac_numengines * -20) + 20; for( $i=0; $i<$ac_numengines; $i++) { $ac_englocx[$i] = $ac_cglocx; $ac_englocy[$i] = $leftmost + ($i * 40); $ac_englocz[$i] = -12.0; } } // aft fuselage engines if ($ac_enginelayout == 2) { $leftmost = ($ac_numengines * -20) + 20; for($i=0; $i<$ac_numengines; $i++) { $ac_englocx[$i] = ($ac_length * $ft_to_in) - 60.0; $ac_englocy[$i] = $leftmost + ($i * 40); $ac_englocz[$i] = 0; } } // wing engines (odd one goes in middle) if ($ac_enginelayout == 3) { $halfcount = intval( $ac_numengines / 2 ); $remainder = $ac_numengines - ($halfcount * 2); for($i=0; $i<$halfcount; $i++) { //left wing $ac_englocx[$i] = $ac_cglocx; $ac_englocy[$i] = $ac_wingspan * -2.0; //span/-2/3*12 $ac_englocz[$i] = -40; } for($j=$i; $j<$halfcount+$remainder; $j++) { //center $ac_englocx[$j] = $ac_cglocx; $ac_englocy[$j] = 0; $ac_englocz[$j] = -20; } for($k=$j; $k<$ac_numengines; $k++) { //right wing $ac_englocx[$k] = $ac_cglocx; $ac_englocy[$k] = $ac_wingspan * 2.0; //span/2/3*12 $ac_englocz[$k] = -40; } } // wing and tail engines if ($ac_enginelayout == 4) { $halfcount = intval( $ac_numengines / 2 ); $remainder = $ac_numengines - ($halfcount * 2); for($i=0; $i<$halfcount; $i++) { //left wing $ac_englocx[$i] = $ac_cglocx; $ac_englocy[$i] = $ac_wingspan * -2.0; //span/-2/3*12 $ac_englocz[$i] = -40; } for($j=$i; $j<$halfcount+$remainder; $j++) { //center $ac_englocx[$j] = $ac_length - 60; $ac_englocy[$j] = 0; $ac_englocz[$j] = 60; } for($k=$j; $i<$ac_numengines; $i++) { //right wing $ac_englocx[$k] = $ac_cglocx; $ac_englocy[$k] = $ac_wingspan * 2.0; //span/2/3*12 $ac_englocz[$k] = -40; } } // wing and nose engines if ($ac_enginelayout == 5) { $halfcount = intval( $ac_numengines / 2 ); $remainder = $ac_numengines - ($halfcount * 2); for($i=0; $i<$halfcount; $i++) { //left wing $ac_englocx[$i] = $ac_cglocx; $ac_englocy[$i] = $ac_wingspan * -2.0; //span/-2/3*12 $ac_englocz[$i] = -40; } for($j=$i; $j<$halfcount+$remainder; $j++) { //center $ac_englocx[$j] = 36.0; $ac_englocy[$j] = 0; $ac_englocz[$j] = 0; } for($k=$j; $i<$ac_numengines; $i++) { //right wing $ac_englocx[$k] = $ac_cglocx; $ac_englocy[$k] = $ac_wingspan * 2.0; //span/2/3*12 $ac_englocz[$k] = -40; } } // thruster goes where engine is for($i=0; $i<$ac_numengines; $i++) { $ac_engpitch[$i] = 0; $ac_engyaw[$i] = 0; $ac_engfeed[$i] = $i; $ac_thrusterlocx[$i] = $ac_englocx[$i]; $ac_thrusterlocy[$i] = $ac_englocy[$i]; $ac_thrusterlocz[$i] = $ac_englocz[$i]; $ac_thrusterpitch[$i] = 0; $ac_thrusteryaw[$i] = 0; } // thruster type (note: only piston engine gets a propeller) switch($ac_enginetype) { case 0: $ac_thrustertype = 'prop'; break; case 1: $ac_thrustertype = 'direct'; break; case 2: $ac_thrustertype = 'direct'; break; case 3: $ac_thrustertype = 'direct'; break; case 4: $ac_thrustertype = 'prop'; break; } //***** FUEL TANKS ********************************** // an N-engined airplane will have N+1 fuel tanks // all tanks located at CG and are half full $ac_tanklocx = $ac_cglocx; $ac_tanklocy = $ac_cglocy; $ac_tanklocz = $ac_cglocz; $ac_tankradius = 1; if($ac_numengines > 0) { switch($ac_type) { case 0: $ac_fuelweight = $ac_weight * 0.079; break; case 1: $ac_fuelweight = $ac_weight * 0.148; break; case 2: $ac_fuelweight = $ac_weight * 0.183; break; case 3: $ac_fuelweight = $ac_weight * 0.122; break; case 4: $ac_fuelweight = $ac_weight * 0.162; break; case 5: $ac_fuelweight = $ac_weight * 0.207; break; case 6: $ac_fuelweight = $ac_weight * 0.277; break; case 7: $ac_fuelweight = $ac_weight * 0.338; break; case 8: $ac_fuelweight = $ac_weight * 0.419; break; case 9: $ac_fuelweight = $ac_weight * 0.254; break; } $ac_tankcapacity = $ac_fuelweight / ($ac_numengines + 1); } else { $ac_tankcapacity = 0; $ac_fuelweight = 0; } $ac_tankcontents = $ac_tankcapacity/2; //***** PAYLOAD ************************************* // A point mass will be placed at the CG weighing // 1/2 of the usable aircraft load. $ac_payloadlocx = $ac_cglocx; $ac_payloadlocy = $ac_cglocy; $ac_payloadlocz = $ac_cglocz; $ac_payload = $ac_weight - $ac_emptyweight - $ac_fuelweight; //***** LIFT **************************************** // estimate slope of lift curve based on airplane type // units: per radian switch($ac_type) { case 0: $ac_CLalpha = 5.5; break; case 1: $ac_CLalpha = 5.0; break; case 2: $ac_CLalpha = 4.8; break; case 3: $ac_CLalpha = 4.5; break; case 4: $ac_CLalpha = 3.5; break; case 5: $ac_CLalpha = 3.6; break; case 6: $ac_CLalpha = 4.4; break; case 7: $ac_CLalpha = 4.4; break; case 8: $ac_CLalpha = 4.4; break; case 9: $ac_CLalpha = 4.9; break; } // estimate CL at zero alpha switch($ac_type) { case 0: $ac_CL0 = 0.25; break; case 1: $ac_CL0 = 0.25; break; case 2: $ac_CL0 = 0.24; break; case 3: $ac_CL0 = 0.17; break; case 4: $ac_CL0 = 0.08; break; case 5: $ac_CL0 = 0.08; break; case 6: $ac_CL0 = 0.20; break; case 7: $ac_CL0 = 0.20; break; case 8: $ac_CL0 = 0.20; break; case 9: $ac_CL0 = 0.24; break; } // estimate stall CL, based on airplane type switch($ac_type) { case 0: $ac_CLmax = 1.40; break; case 1: $ac_CLmax = 1.40; break; case 2: $ac_CLmax = 1.30; break; case 3: $ac_CLmax = 1.20; break; case 4: $ac_CLmax = 1.00; break; case 5: $ac_CLmax = 1.00; break; case 6: $ac_CLmax = 1.20; break; case 7: $ac_CLmax = 1.20; break; case 8: $ac_CLmax = 1.20; break; case 9: $ac_CLmax = 1.40; break; } // estimate delta-CL-flaps, based on airplane type switch($ac_type) { case 0: $ac_dCLflaps = 0.200; break; case 1: $ac_dCLflaps = 0.400; break; case 2: $ac_dCLflaps = 0.400; break; case 3: $ac_dCLflaps = 0.300; break; case 4: $ac_dCLflaps = 0.350; break; case 5: $ac_dCLflaps = 0.350; break; case 6: $ac_dCLflaps = 1.500; break; case 7: $ac_dCLflaps = 1.500; break; case 8: $ac_dCLflaps = 1.500; break; case 9: $ac_dCLflaps = 0.600; break; } // some types have speedbrakes in wings, affecting lift switch($ac_type) { case 0: $ac_dCLspeedbrake = -0.05; break; case 1: $ac_dCLspeedbrake = 0.00; break; case 2: $ac_dCLspeedbrake = 0.00; break; case 3: $ac_dCLspeedbrake = 0.00; break; case 4: $ac_dCLspeedbrake = 0.00; break; case 5: $ac_dCLspeedbrake = 0.00; break; case 6: $ac_dCLspeedbrake = -0.10; break; case 7: $ac_dCLspeedbrake = -0.09; break; case 8: $ac_dCLspeedbrake = -0.08; break; case 9: $ac_dCLspeedbrake = 0.00; break; } // estimate lift due to elevator deflection $ac_CLde = 0.2; //***** DRAG ***************************************** // estimate drag at zero lift, based on airplane type // NOT including landing gear switch($ac_type) { case 0: $ac_CD0 = 0.010; break; case 1: $ac_CD0 = 0.024; break; case 2: $ac_CD0 = 0.025; break; case 3: $ac_CD0 = 0.020; break; case 4: $ac_CD0 = 0.021; break; case 5: $ac_CD0 = 0.024; break; case 6: $ac_CD0 = 0.020; break; case 7: $ac_CD0 = 0.019; break; case 8: $ac_CD0 = 0.017; break; case 9: $ac_CD0 = 0.025; break; } // add gear drag if fixed gear if($ac_gearretract == 0) { switch($ac_type) { case 0: $ac_CD0 += 0.002; break; case 1: $ac_CD0 += 0.004; break; case 2: $ac_CD0 += 0.004; break; case 3: $ac_CD0 += 0.004; break; case 4: $ac_CD0 += 0.005; break; case 5: $ac_CD0 += 0.005; break; case 6: $ac_CD0 += 0.002; break; case 7: $ac_CD0 += 0.002; break; case 8: $ac_CD0 += 0.002; break; case 9: $ac_CD0 += 0.003; break; } } // estimate induced drag coefficient K switch($ac_type) { case 0: $ac_K = 0.023; break; case 1: $ac_K = 0.040; break; case 2: $ac_K = 0.041; break; case 3: $ac_K = 0.060; break; case 4: $ac_K = 0.120; break; case 5: $ac_K = 0.120; break; case 6: $ac_K = 0.043; break; case 7: $ac_K = 0.042; break; case 8: $ac_K = 0.042; break; case 9: $ac_K = 0.039; break; } // CD flaps switch($ac_type) { case 0: $ac_CDflaps = 0.024; break; case 1: $ac_CDflaps = 0.030; break; case 2: $ac_CDflaps = 0.039; break; case 3: $ac_CDflaps = 0.040; break; case 4: $ac_CDflaps = 0.080; break; case 5: $ac_CDflaps = 0.075; break; case 6: $ac_CDflaps = 0.059; break; case 7: $ac_CDflaps = 0.057; break; case 8: $ac_CDflaps = 0.055; break; case 9: $ac_CDflaps = 0.035; break; } // estimate drag from landing gear down switch($ac_type) { case 0: $ac_CDgear = 0.012; break; case 1: $ac_CDgear = 0.030; break; case 2: $ac_CDgear = 0.030; break; case 3: $ac_CDgear = 0.030; break; case 4: $ac_CDgear = 0.020; break; case 5: $ac_CDgear = 0.020; break; case 6: $ac_CDgear = 0.015; break; case 7: $ac_CDgear = 0.013; break; case 8: $ac_CDgear = 0.011; break; case 9: $ac_CDgear = 0.023; break; } $ac_CDde = 0.04; // elevator deflection $ac_CDbeta = 0.2; // sideslip $ac_CDspeedbrake = $ac_CD0; // speedbrake // estimate critical mach, based on airplane type switch($ac_type) { case 0: $ac_Mcrit = 0.70; break; case 1: $ac_Mcrit = 0.70; break; case 2: $ac_Mcrit = 0.72; break; case 3: $ac_Mcrit = 0.75; break; case 4: $ac_Mcrit = 0.81; break; case 5: $ac_Mcrit = 0.81; break; case 6: $ac_Mcrit = 0.79; break; case 7: $ac_Mcrit = 0.79; break; case 8: $ac_Mcrit = 0.79; break; case 9: $ac_Mcrit = 0.70; break; } //***** SIDE ************************************* // estimate side force due to sideslip (beta) $ac_CYbeta = -1; //***** ROLL ************************************* // estimate roll coefficients $ac_Clbeta = -0.1; // sideslip $ac_Clp = -0.4; // roll rate $ac_Clr = 0.15; // yaw rate switch($ac_type) { // aileron case 0: $ac_Clda = 0.06; break; case 1: $ac_Clda = 0.17; break; case 2: $ac_Clda = 0.17; break; case 3: $ac_Clda = 0.18; break; case 4: $ac_Clda = 0.11; break; case 5: $ac_Clda = 0.12; break; case 6: $ac_Clda = 0.10; break; case 7: $ac_Clda = 0.10; break; case 8: $ac_Clda = 0.10; break; case 9: $ac_Clda = 0.15; break; } $ac_Cldr = 0.01; // rudder deflection //***** PITCH ************************************ // estimate pitch coefficients switch($ac_type) { case 0: // glider $ac_Cmalpha = -0.5; // per radian alpha $ac_Cmde = -0.8; // elevator deflection $ac_Cmq = -9.0; // pitch rate $ac_Cmadot = -12.0; // alpha-dot break; case 1: // light single $ac_Cmalpha = -0.5; // per radian alpha $ac_Cmde = -1.1; // elevator deflection $ac_Cmq = -12.0; // pitch rate $ac_Cmadot = -7.0; // alpha-dot break; case 2: // light twin $ac_Cmalpha = -0.4; // per radian alpha $ac_Cmde = -1.0; // elevator deflection $ac_Cmq = -22.0; // pitch rate $ac_Cmadot = -8.0; // alpha-dot break; case 3: // WWII fighter/racer/aerobatic $ac_Cmalpha = -0.5; // per radian alpha $ac_Cmde = -1.0; // elevator deflection $ac_Cmq = -15.0; // pitch rate $ac_Cmadot = -7.0; // alpha-dot break; case 4: // single engine jet fighter $ac_Cmalpha = -0.3; // per radian alpha $ac_Cmde = -0.8; // elevator deflection $ac_Cmq = -18.0; // pitch rate $ac_Cmadot = -9.0; // alpha-dot break; case 5: // two engine jet fighter $ac_Cmalpha = -0.3; // per radian alpha $ac_Cmde = -0.8; // elevator deflection $ac_Cmq = -18.0; // pitch rate $ac_Cmadot = -9.0; // alpha-dot break; case 6: // two engine jet transport $ac_Cmalpha = -0.6; // per radian alpha $ac_Cmde = -1.2; // elevator deflection $ac_Cmq = -17.0; // pitch rate $ac_Cmadot = -6.0; // alpha-dot break; case 7: // three engine jet transport $ac_Cmalpha = -0.6; // per radian alpha $ac_Cmde = -1.2; // elevator deflection $ac_Cmq = -17.0; // pitch rate $ac_Cmadot = -6.0; // alpha-dot break; case 8: // four+ engine jet transport $ac_Cmalpha = -0.7; // per radian alpha $ac_Cmde = -1.3; // elevator deflection $ac_Cmq = -21.0; // pitch rate $ac_Cmadot = -4.0; // alpha-dot break; case 9: // multi-engine prop transport $ac_Cmalpha = -0.4; // per radian alpha $ac_Cmde = -1.0; // elevator deflection $ac_Cmq = -22.0; // pitch rate $ac_Cmadot = -8.0; // alpha-dot break; } //***** YAW ************************************** // estimate yaw coefficients $ac_Cnbeta = 0.12; // sideslip $ac_Cnr = -0.15; // yaw rate $ac_Cndr = -0.10; // rudder deflection if($ac_type == 0) $ac_Cndr = -0.03; // glider switch($ac_type) { // adverse yaw case 0: $ac_Cnda = -0.02; break; case 1: $ac_Cnda = -0.01; break; case 2: $ac_Cnda = -0.01; break; case 3: $ac_Cnda = -0.003; break; case 4: $ac_Cnda = 0.0; break; case 5: $ac_Cnda = 0.0; break; case 6: $ac_Cnda = 0.0; break; case 7: $ac_Cnda = 0.0; break; case 8: $ac_Cnda = 0.0; break; case 9: $ac_Cnda = -0.008; break; } // get the server date/time $date_string = date('Y-m-d'); //************************************************ //* * //* Print out xml document * //* * //************************************************ print("\n"); print("\n"); print("\n\n"); print(" \n"); print(" Aeromatic v $version \n"); print(" $date_string\n"); print(" \$Revision: 1.16 $\n"); print(" Models a $ac_name. \n"); print(" \n\n"); print("\n\n"); //***** METRICS ********************************** print(" \n"); printf(" %7.2f \n", $ac_wingarea); printf(" %7.2f \n", $ac_wingspan); printf(" %7.2f \n", $ac_wingincidence); printf(" %7.2f \n", $ac_wingchord); printf(" %7.2f \n", $ac_htailarea); printf(" %7.2f \n", $ac_htailarm); printf(" %7.2f \n", $ac_vtailarea); printf(" %7.2f \n", $ac_vtailarm); print(" \n"); printf(" %6.2f \n", $ac_aerorpx); printf(" %6.2f \n", $ac_aerorpy); printf(" %6.2f \n", $ac_aerorpz); print(" \n"); print(" \n"); printf(" %6.2f \n", $ac_eyeptlocx); printf(" %6.2f \n", $ac_eyeptlocy); printf(" %6.2f \n", $ac_eyeptlocz); print(" \n"); print(" \n"); print(" 0\n"); print(" 0\n"); print(" 0\n"); print(" \n"); print(" \n\n"); print(" \n"); printf(" %8.0f \n", $ac_ixx); printf(" %8.0f \n", $ac_iyy); printf(" %8.0f \n", $ac_izz); //printf(" %8.0f \n", $ac_ixy); //printf(" %8.0f \n", $ac_ixz); //printf(" %8.0f \n", $ac_iyz); printf(" %8.0f \n", $ac_emptyweight); print( " \n"); printf(" %6.2f \n", $ac_cglocx); printf(" %6.2f \n", $ac_cglocy); printf(" %6.2f \n", $ac_cglocz); print( " \n"); print( " \n"); printf(" %2.0f LBS + full (%2.0f LBS) fuel should bring model up to entered max weight\n", $ac_payload, $ac_fuelweight); printf(" %8.1f \n", $ac_payload * .5); print( " \n"); printf(" %6.2f \n", $ac_payloadlocx); printf(" %6.2f \n", $ac_payloadlocy); printf(" %6.2f \n", $ac_payloadlocz); print( " \n"); print( " \n"); print(" \n\n"); //***** LANDING GEAR ****************************** print(" \n\n"); if($ac_type == 0) { // if this is a glider print(" \n"); print(" \n"); printf(" %6.2f \n", $ac_gearlocx_main); printf(" %6.2f \n", -$ac_gearlocy_main); printf(" %6.2f \n", $ac_gearlocz_main); print(" \n"); printf(" %4.3f \n", $ac_gearstatic); printf(" %4.3f \n", $ac_geardynamic); printf(" %4.3f \n", $ac_gearrolling); printf(" %8.2f \n", $ac_gearspring_main); printf(" %8.2f \n", $ac_geardamp_main); print(" 0\n"); print(" NONE\n"); print(" $ac_retract\n"); print(" \n\n"); print(" \n"); print(" \n"); printf(" %6.2f \n", $ac_gearlocx_main); printf(" %6.2f \n", $ac_gearlocy_main); printf(" %6.2f \n", $ac_gearlocz_main); print(" \n"); printf(" %4.3f \n", $ac_gearstatic); printf(" %4.3f \n", $ac_geardynamic); printf(" %4.3f \n", $ac_gearrolling); printf(" %8.2f \n", $ac_gearspring_main); printf(" %8.2f \n", $ac_geardamp_main); print(" 0\n"); print(" NONE\n"); print(" $ac_retract\n"); print(" \n\n"); print(" \n"); print(" \n"); printf(" %6.2f \n", $ac_gearlocx_nose); printf(" %6.2f \n", $ac_gearlocy_nose); printf(" %6.2f \n", $ac_gearlocz_nose); print(" \n"); printf(" %4.3f \n", $ac_gearstatic); printf(" %4.3f \n", $ac_geardynamic); printf(" %4.3f \n", $ac_gearrolling); printf(" %8.2f \n", $ac_gearspring_nose); printf(" %8.2f \n", $ac_geardamp_nose); print(" 0\n"); print(" NONE\n"); print(" $ac_retract\n"); print(" \n\n"); print(" \n"); print(" \n"); printf(" %6.2f \n", $ac_cglocx); printf(" %6.2f \n", -$ac_halfspan * $ft_to_in); printf(" %6.2f \n", $ac_cglocz); print(" \n"); printf(" %2.2f \n", 1.0); printf(" %2.2f \n", 1.0); printf(" %8.2f \n", $ac_gearspring_main); printf(" %8.2f \n", $ac_gearspring_main); print(" \n\n"); print(" \n"); print(" \n"); printf(" %6.2f \n", $ac_cglocx); printf(" %6.2f \n", $ac_halfspan * $ft_to_in); printf(" %6.2f \n", $ac_cglocz); print(" \n"); printf(" %2.2f \n", 1.0); printf(" %2.2f \n", 1.0); printf(" %8.2f \n", $ac_gearspring_main); printf(" %8.2f \n", $ac_gearspring_main); print(" \n\n"); } else { if ($ac_geartype == 0) { // if this is a tricycle gear print(" \n"); print(" \n"); printf(" %6.2f \n", $ac_gearlocx_nose); printf(" %6.2f \n", $ac_gearlocy_nose); printf(" %6.2f \n", $ac_gearlocz_nose); print(" \n"); printf(" %2.2f \n", $ac_gearstatic); printf(" %2.2f \n", $ac_geardynamic); printf(" %2.2f \n", $ac_gearrolling); printf(" %8.2f \n", $ac_gearspring_nose); printf(" %8.2f \n", $ac_geardamp_nose); printf(" %2.2f \n", $ac_gearmaxsteer); print(" NONE\n"); print(" $ac_retract\n"); print(" \n\n"); } print(" \n"); print(" \n"); printf(" %6.2f \n", $ac_gearlocx_main); printf(" %6.2f \n", -$ac_gearlocy_main); printf(" %6.2f \n", $ac_gearlocz_main); print(" \n"); printf(" %2.2f \n", $ac_gearstatic); printf(" %2.2f \n", $ac_geardynamic); printf(" %2.2f \n", $ac_gearrolling); printf(" %8.2f \n", $ac_gearspring_main); printf(" %8.2f \n", $ac_geardamp_main); print(" 0\n"); print(" LEFT\n"); print(" $ac_retract\n"); print(" \n\n"); print(" \n"); print(" \n"); printf(" %6.2f \n", $ac_gearlocx_main); printf(" %6.2f \n", $ac_gearlocy_main); printf(" %6.2f \n", $ac_gearlocz_main); print(" \n"); printf(" %2.2f \n", $ac_gearstatic); printf(" %2.2f \n", $ac_geardynamic); printf(" %2.2f \n", $ac_gearrolling); printf(" %8.2f \n", $ac_gearspring_main); printf(" %8.2f \n", $ac_geardamp_main); print(" 0\n"); print(" RIGHT\n"); print(" $ac_retract\n"); print(" \n\n"); if ($ac_geartype == 1) { // if this is a taildragger print(" \n"); print(" \n"); printf(" %6.2f \n", $ac_gearlocx_tail); printf(" %6.2f \n", $ac_gearlocy_tail); printf(" %6.2f \n", $ac_gearlocz_tail); print(" \n"); printf(" %2.2f \n", $ac_gearstatic); printf(" %2.2f \n", $ac_geardynamic); printf(" %2.2f \n", $ac_gearrolling); printf(" %8.2f \n", $ac_gearspring_tail); printf(" %8.2f \n", $ac_geardamp_tail); printf(" %2.2f \n", $ac_gearmaxsteer); print(" NONE\n"); print(" $ac_retract\n"); print(" \n\n"); } print(" \n"); print(" \n"); printf(" %6.2f \n", $ac_cglocx); printf(" %6.2f \n", -$ac_halfspan); printf(" %6.2f \n", $ac_cglocz); print(" \n"); printf(" %2.2f \n", 1.0); printf(" %2.2f \n", 1.0); printf(" %8.2f \n", $ac_gearspring_main); printf(" %8.2f \n", $ac_gearspring_main); print(" \n\n"); print(" \n"); print(" \n"); printf(" %6.2f \n", $ac_cglocx); printf(" %6.2f \n", $ac_halfspan); printf(" %6.2f \n", $ac_cglocz); print(" \n"); printf(" %2.2f \n", 1.0); printf(" %2.2f \n", 1.0); printf(" %8.2f \n", $ac_gearspring_main); printf(" %8.2f \n", $ac_gearspring_main); print(" \n\n"); } print(" \n\n"); //***** PROPULSION *************************************** $ac_engine_name = $ac_name . '_engine'; $ac_prop_name = $ac_name . '_prop'; print(" \n\n"); for($i=0; $i<$ac_numengines; $i++) { print(" \n"); print(" \n"); printf(" %6.2f \n", $ac_englocx[$i]); printf(" %6.2f \n", $ac_englocy[$i]); printf(" %6.2f \n", $ac_englocz[$i]); print(" \n"); print(" \n"); printf(" %2.2f \n", $ac_engpitch[$i]); print(" 0.00 \n"); printf(" %2.2f \n", $ac_engyaw[$i]); print(" \n"); print(" $ac_engfeed[$i]\n"); if($ac_enginetype == 0) { print(" \n"); print(" 1 \n"); } else { print(" \n"); } print(" \n"); printf(" %6.2f \n", $ac_thrusterlocx[$i]); printf(" %6.2f \n", $ac_thrusterlocy[$i]); printf(" %6.2f \n", $ac_thrusterlocz[$i]); print(" \n"); print(" \n"); printf(" %2.2f \n", $ac_thrusterpitch[$i]); print(" 0.00 \n"); printf(" %2.2f \n", $ac_thrusteryaw[$i]); print(" \n"); print(" \n"); print(" \n\n"); } //***** FUEL TANKS ************************************** if($ac_numengines > 0) { // Don't create fuel if there is no engine for($i=0; $i<($ac_numengines + 1); $i++) { print(" \n"); print(" \n"); printf(" %6.2f \n", $ac_tanklocx); printf(" %6.2f \n", $ac_tanklocy); printf(" %6.2f \n", $ac_tanklocz); print(" \n"); printf(" %6.2f \n", $ac_tankcapacity); printf(" %6.2f \n", $ac_tankcontents); print(" \n\n"); } } print(" \n\n"); //***** FLIGHT CONTROL SYSTEM *************************** print(" \n\n"); print(" \n\n"); print(" \n"); print(" fcs/elevator-cmd-norm\n"); print(" fcs/pitch-trim-cmd-norm\n"); print(" \n"); print(" -1 \n"); print(" 1 \n"); print(" \n"); print(" \n\n"); print(" \n"); print(" fcs/pitch-trim-sum\n"); print(" \n"); print(" -0.35 \n"); print(" 0.35 \n"); print(" \n"); print("

fcs/elevator-pos-rad

\n"); print(" \n\n"); print(" \n"); print(" fcs/elevator-pos-rad\n"); print(" \n"); print(" -0.35 \n"); print(" 0.35 \n"); print(" \n"); print(" \n"); print(" -1 \n"); print(" 1 \n"); print(" \n"); print("

fcs/elevator-pos-norm

\n"); print(" \n\n"); print(" \n\n"); print(" \n\n"); print(" \n"); print(" fcs/aileron-cmd-norm\n"); print(" fcs/roll-trim-cmd-norm\n"); print(" \n"); print(" -1 \n"); print(" 1 \n"); print(" \n"); print(" \n\n"); print(" \n"); print(" fcs/roll-trim-sum\n"); print(" \n"); print(" -0.35 \n"); print(" 0.35 \n"); print(" \n"); print("

fcs/left-aileron-pos-rad

\n"); print(" \n\n"); print(" \n"); print(" fcs/roll-trim-sum\n"); print(" \n"); print(" -0.35 \n"); print(" 0.35 \n"); print(" \n"); print("

fcs/right-aileron-pos-rad

\n"); print(" \n\n"); print(" \n"); print(" fcs/left-aileron-pos-rad\n"); print(" \n"); print(" -0.35 \n"); print(" 0.35 \n"); print(" \n"); print(" \n"); print(" -1 \n"); print(" 1 \n"); print(" \n"); print("

fcs/left-aileron-pos-norm

\n"); print(" \n\n"); print(" \n"); print(" fcs/right-aileron-pos-rad\n"); print(" \n"); print(" -0.35 \n"); print(" 0.35 \n"); print(" \n"); print(" \n"); print(" -1 \n"); print(" 1 \n"); print(" \n"); print("

fcs/right-aileron-pos-norm

\n"); print(" \n\n"); print(" \n\n"); if($ac_yawdamper == 1) { print(" fcs/yaw-damper-enable\n"); } print(" \n\n"); print(" \n"); print(" fcs/rudder-cmd-norm\n"); print(" fcs/yaw-trim-cmd-norm\n"); print(" \n"); print(" -1 \n"); print(" 1 \n"); print(" \n"); print(" \n\n"); if($ac_yawdamper == 1) { print(" \n"); print(" velocities/r-aero-rad_sec\n"); print(" \n"); print(" velocities/ve-kts\n"); print(" \n"); print(" 30 0.00\n"); print(" 60 2.00\n"); print(" \n"); print(" \n"); print(" fcs/yaw-damper-enable\n"); print(" \n\n"); print(" \n"); print(" fcs/rudder-command-sum\n"); print(" fcs/yaw-damper-rate\n"); print(" \n"); print(" -1.1 \n"); print(" 1.1 \n"); print(" \n"); print(" \n\n"); print(" \n"); print(" fcs/rudder-sum\n"); print(" \n"); print(" -1.1 \n"); print(" 1.1 \n"); print(" \n"); print(" \n"); print(" -0.35 \n"); print(" 0.35 \n"); print(" \n"); print("

fcs/rudder-pos-rad

\n"); print(" \n\n"); } else { print(" \n"); print(" fcs/rudder-command-sum\n"); print(" \n"); print(" -0.35 \n"); print(" 0.35 \n"); print(" \n"); print("

fcs/rudder-pos-rad

\n"); print(" \n\n"); } print(" \n"); print(" fcs/rudder-pos-rad\n"); print(" \n"); print(" -0.35 \n"); print(" 0.35 \n"); print(" \n"); print(" \n"); print(" -1 \n"); print(" 1 \n"); print(" \n"); print("

fcs/rudder-pos-norm

\n"); print(" \n\n"); print(" \n\n"); print(" \n"); print(" \n"); print(" fcs/flap-cmd-norm\n"); print(" \n"); print(" \n"); print(" 0 \n"); print(" 0 \n"); print(" \n"); print(" \n"); print(" 15 \n"); print(" 4 \n"); print(" \n"); print(" \n"); print(" 30 \n"); print(" 3 \n"); print(" \n"); print(" \n"); print("

fcs/flap-pos-deg

\n"); print(" \n\n"); print(" \n"); print(" fcs/flap-pos-deg\n"); print(" \n"); print(" 0 \n"); print(" 30 \n"); print(" \n"); print(" \n"); print(" 0 \n"); print(" 1 \n"); print(" \n"); print("

fcs/flap-pos-norm

\n"); print(" \n\n"); print(" \n\n"); print(" \n"); if($ac_gearretract == 1) { print(" \n"); print(" gear/gear-cmd-norm\n"); print(" \n"); print(" \n"); print(" 0 \n"); print(" 0 \n"); print(" \n"); print(" \n"); print(" 1 \n"); print(" 5 \n"); print(" \n"); print(" \n"); print("

gear/gear-pos-norm

\n"); print(" \n\n"); } print(" \n\n"); print(" \n"); print(" \n"); print(" fcs/speedbrake-cmd-norm\n"); print(" \n"); print(" \n"); print(" 0 \n"); print(" 0 \n"); print(" \n"); print(" \n"); print(" 1 \n"); print(" 1 \n"); print(" \n"); print(" \n"); print("

fcs/speedbrake-pos-norm

\n"); print(" \n\n"); print(" \n\n"); print(" \n\n"); //***** AERODYNAMICS ****************************************** print(" \n\n"); //print(" \n"); //print(" Aeromatic version $version\n"); //print(" \n\n"); print(" \n\n"); // build a lift curve with four points print(" \n"); print(" Lift due to alpha\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" \n"); print(" aero/alpha-rad\n"); print(" \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(" \n"); print(" \n\n"); $ac_dCLflap_per_deg = $ac_dCLflaps / 30.0; print(" \n"); print(" Delta Lift due to flaps\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" fcs/flap-pos-deg\n"); printf(" %6.5f \n", $ac_dCLflap_per_deg); print(" \n"); print(" \n\n"); print(" \n"); print(" Delta Lift due to speedbrake\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" fcs/speedbrake-pos-norm\n"); print(" $ac_dCLspeedbrake\n"); print(" \n"); print(" \n\n"); print(" \n"); print(" Lift due to Elevator Deflection\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" fcs/elevator-pos-rad\n"); print(" $ac_CLde\n"); print(" \n"); print(" \n\n"); print(" \n\n"); //***** DRAG ****************************************************** print(" \n\n"); print(" \n"); print(" Drag at zero lift\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" \n"); print(" aero/alpha-rad\n"); print(" \n"); print( " -1.57 1.500\n"); $ac_CD02 = $ac_CD0 * 1.3; 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(" \n"); print(" \n\n"); print(" \n"); print(" Induced drag\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" aero/cl-squared\n"); print(" $ac_K\n"); print(" \n"); print(" \n\n"); print(" \n"); print(" Drag due to mach\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" \n"); print(" velocities/mach\n"); print(" \n"); print(" 0.00 0.000\n"); print(" $ac_Mcrit 0.000\n"); print(" 1.10 0.023\n"); print(" 1.80 0.015\n"); print(" \n"); print(" \n"); print(" \n"); print(" \n\n"); $ac_CDflaps_per_deg = $ac_CDflaps / 30.0; print(" \n"); print(" Drag due to flaps\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" fcs/flap-pos-deg\n"); printf(" %6.5f \n", $ac_CDflaps_per_deg); print(" \n"); print(" \n\n"); if($ac_gearretract == 1) { print(" \n"); print(" Drag due to gear\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" gear/gear-pos-norm\n"); print(" $ac_CDgear\n"); print(" \n"); print(" \n\n"); } print(" \n"); print(" Drag due to speedbrakes\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" fcs/speedbrake-pos-norm\n"); print(" $ac_CDspeedbrake\n"); print(" \n"); print(" \n\n"); print(" \n"); print(" Drag due to sideslip\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" \n"); print(" aero/beta-rad\n"); print(" \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 0.000\n"); printf(" 0.26 %4.3f\n", $ac_CDb26); print( " 1.57 1.230\n"); print(" \n"); print(" \n"); print(" \n"); print(" \n\n"); print(" \n"); print(" Drag due to Elevator Deflection\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" fcs/elevator-pos-norm\n"); print(" $ac_CDde\n"); print(" \n"); print(" \n\n"); print(" \n\n"); //***** SIDE ************************************************* print(" \n\n"); print(" \n"); print(" Side force due to beta\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" aero/beta-rad\n"); print(" $ac_CYbeta\n"); print(" \n"); print(" \n\n"); print(" \n\n"); //***** ROLL ************************************************ print(" \n\n"); print(" \n"); print(" Roll moment due to beta\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" metrics/bw-ft\n"); print(" aero/beta-rad\n"); print(" $ac_Clbeta\n"); print(" \n"); print(" \n\n"); print(" \n"); print(" Roll moment due to roll rate\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" metrics/bw-ft\n"); print(" aero/bi2vel\n"); print(" velocities/p-aero-rad_sec\n"); print(" $ac_Clp\n"); print(" \n"); print(" \n\n"); print(" \n"); print(" Roll moment due to yaw rate\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" metrics/bw-ft\n"); print(" aero/bi2vel\n"); print(" velocities/r-aero-rad_sec\n"); print(" $ac_Clr\n"); print(" \n"); print(" \n\n"); print(" \n"); print(" Roll moment due to aileron\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" metrics/bw-ft\n"); print(" fcs/left-aileron-pos-rad\n"); print(" $ac_Clda\n"); print(" \n"); print(" \n\n"); print(" \n"); print(" Roll moment due to rudder\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" metrics/bw-ft\n"); print(" fcs/rudder-pos-rad\n"); print(" $ac_Cldr\n"); print(" \n"); print(" \n\n"); print(" \n\n"); //***** PITCH ***************************************** print(" \n\n"); print(" \n"); print(" Pitch moment due to alpha\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" metrics/cbarw-ft\n"); print(" aero/alpha-rad\n"); print(" $ac_Cmalpha\n"); print(" \n"); print(" \n\n"); print(" \n"); print(" Pitch moment due to elevator\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" metrics/cbarw-ft\n"); print(" fcs/elevator-pos-rad\n"); print(" \n"); print(" velocities/mach\n"); print(" \n"); printf(" 0.0 %4.3f\n", $ac_Cmde); $ac_Cmde4 = $ac_Cmde * 0.25; printf(" 2.0 %4.3f\n", $ac_Cmde4); print(" \n"); print(" \n"); print(" \n"); print(" \n\n"); print(" \n"); print(" Pitch moment due to pitch rate\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" metrics/cbarw-ft\n"); print(" aero/ci2vel\n"); print(" velocities/q-aero-rad_sec\n"); print(" $ac_Cmq\n"); print(" \n"); print(" \n\n"); print(" \n"); print(" Pitch moment due to alpha rate\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" metrics/cbarw-ft\n"); print(" aero/ci2vel\n"); print(" aero/alphadot-rad_sec\n"); print(" $ac_Cmadot\n"); print(" \n"); print(" \n\n"); print(" \n\n"); //***** YAW *********************************************** print(" \n\n"); print(" \n"); print(" Yaw moment due to beta\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" metrics/bw-ft\n"); print(" aero/beta-rad\n"); print(" $ac_Cnbeta\n"); print(" \n"); print(" \n\n"); print(" \n"); print(" Yaw moment due to yaw rate\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" metrics/bw-ft\n"); print(" aero/bi2vel\n"); print(" velocities/r-aero-rad_sec\n"); print(" $ac_Cnr\n"); print(" \n"); print(" \n\n"); print(" \n"); print(" Yaw moment due to rudder\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" metrics/bw-ft\n"); print(" fcs/rudder-pos-rad\n"); print(" $ac_Cndr\n"); print(" \n"); print(" \n\n"); print(" \n"); print(" Adverse yaw\n"); print(" \n"); print(" aero/qbar-psf\n"); print(" metrics/Sw-sqft\n"); print(" metrics/bw-ft\n"); print(" fcs/left-aileron-pos-rad\n"); print(" $ac_Cnda\n"); print(" \n"); print(" \n\n"); print(" \n\n"); print(" \n\n"); print(" \n"); print(" \n\n"); print("\n"); ?>