\n");
print("\n\n");
switch ($ac_enginetype) {
case 0: MakePiston(); break;
case 1: MakeTurbine(); break;
case 2: MakeTurboprop(); break;
case 3: MakeRocket(); break;
}
//************************************************
//* MakePiston() *
//************************************************
function MakePiston() {
global $ac_enginename, $ac_enginepower;
$displacement = $ac_enginepower * 1.9;
$stroke = 4.375; // FIXME: we can use maxrpm to find a stroke length
$bore = 5.125;
$bore_s = pow($bore/2, 2.0) * 3.14159; // Guess the area of one piston (5.125/2)^2 * PI
$n_cylinders = $displacement / ($stroke * $bore_s);
$n_cylinders = (($n_cylinders < 1) ? 1 : floor($n_cylinders+0.5));
print ("\n");
print (" 10.0 \n");
print (" 28.5 \n");
printf(" %3.2f \n", $displacement);
printf(" %3.2f \n", $ac_enginepower);
print (" 4.0 \n");
print (" 700.0 \n");
print (" 2800.0 \n");
print (" 0.1 \n");
print (" 0.85 \n");
print (" 0.1 \n");
printf(" %3.2f \n", $ac_enginepower * 0.005);
printf(" %3.2f \n", $ac_enginepower * 0.8);
print (" 1400 \n");
print (" \n");
print (" \n");
printf(" %5.3f \n", $stroke);
printf(" %5.3f \n", $bore);
printf(" %3.1f \n", $n_cylinders);
print (" 8.0 \n");
print ("\n");
}
//************************************************
//* MakeTurbine() *
//************************************************
function MakeTurbine() {
global $ac_enginename, $ac_enginepower,
$ac_augmented, $ac_injected;
if ($ac_augmented) {
$ac_maxthrust = $ac_enginepower * 1.5;
} else {
$ac_maxthrust = $ac_enginepower;
}
print("\n");
printf(" %8.1f \n", $ac_enginepower);
if ($ac_augmented) {
printf(" %8.1f \n", $ac_maxthrust);
}
print(" 1.0 \n");
print(" 0.8 \n");
if ($ac_augmented) {
print(" 1.7 \n");
}
print(" 0.03\n");
print(" 30.0 \n");
print(" 60.0 \n");
print(" 100.0 \n");
print(" 100.0 \n");
if($ac_augmented == 1) {
print(" 1 \n");
print(" 1 \n");
}else {
print(" 0 \n");
}
if($ac_injected == 1) {
print(" 1 \n");
}else {
print(" 0 \n");
}
print("\n");
print(" \n");
print(" \n");
print(" velocities/mach\n");
print(" atmosphere/density-altitude\n");
print(" \n");
print(" -10000 0 10000 20000 30000 40000 50000 60000\n");
print(" 0.0 0.0430 0.0488 0.0528 0.0694 0.0899 0.1183 0.1467 0\n");
print(" 0.2 0.0500 0.0501 0.0335 0.0544 0.0797 0.1049 0.1342 0\n");
print(" 0.4 0.0040 0.0047 0.0020 0.0272 0.0595 0.0891 0.1203 0\n");
print(" 0.6 0.0 0.0 0.0 0.0 0.0276 0.0718 0.1073 0\n");
print(" 0.8 0.0 0.0 0.0 0.0 0.0474 0.0868 0.0900 0\n");
print(" 1.0 0.0 0.0 0.0 0.0 0.0 0.0552 0.0800 0\n");
print(" \n");
print("
\n");
print(" \n\n");
print(" \n");
print(" \n");
print(" velocities/mach\n");
print(" atmosphere/density-altitude\n");
print(" \n");
print(" -10000 0 10000 20000 30000 40000 50000 60000\n");
print(" 0.0 1.2600 1.0000 0.7400 0.5340 0.3720 0.2410 0.1490 0\n");
print(" 0.2 1.1710 0.9340 0.6970 0.5060 0.3550 0.2310 0.1430 0\n");
print(" 0.4 1.1500 0.9210 0.6920 0.5060 0.3570 0.2330 0.1450 0\n");
print(" 0.6 1.1810 0.9510 0.7210 0.5320 0.3780 0.2480 0.1540 0\n");
print(" 0.8 1.2580 1.0200 0.7820 0.5820 0.4170 0.2750 0.1700 0\n");
print(" 1.0 1.3690 1.1200 0.8710 0.6510 0.4750 0.3150 0.1950 0\n");
print(" 1.2 1.4850 1.2300 0.9750 0.7440 0.5450 0.3640 0.2250 0\n");
print(" 1.4 1.5941 1.3400 1.0860 0.8450 0.6280 0.4240 0.2630 0\n");
print(" \n");
print("
\n");
print(" \n\n");
if ($ac_augmented) {
print(" \n");
print(" \n");
print(" velocities/mach\n");
print(" atmosphere/density-altitude\n");
print(" \n");
print(" -10000 0 10000 20000 30000 40000 50000 60000\n");
print(" 0.0 1.1816 1.0000 0.8184 0.6627 0.5280 0.3756 0.2327 0\n");
print(" 0.2 1.1308 0.9599 0.7890 0.6406 0.5116 0.3645 0.2258 0\n");
print(" 0.4 1.1150 0.9474 0.7798 0.6340 0.5070 0.3615 0.2240 0\n");
print(" 0.6 1.1284 0.9589 0.7894 0.6420 0.5134 0.3661 0.2268 0\n");
print(" 0.8 1.1707 0.9942 0.8177 0.6647 0.5309 0.3784 0.2345 0\n");
print(" 1.0 1.2411 1.0529 0.8648 0.7017 0.5596 0.3983 0.2467 0\n");
print(" 1.2 1.3287 1.1254 0.9221 0.7462 0.5936 0.4219 0.2614 0\n");
print(" 1.4 1.4365 1.2149 0.9933 0.8021 0.6360 0.4509 0.2794 0\n");
print(" 1.6 1.5711 1.3260 1.0809 0.8700 0.6874 0.4860 0.3011 0\n");
print(" 1.8 1.7301 1.4579 1.1857 0.9512 0.7495 0.5289 0.3277 0\n");
print(" 2.0 1.8314 1.5700 1.3086 1.0474 0.8216 0.5786 0.3585 0\n");
print(" 2.2 1.9700 1.6900 1.4100 1.2400 0.9100 0.6359 0.3940 0\n");
print(" 2.4 2.0700 1.8000 1.5300 1.3400 1.0000 0.7200 0.4600 0\n");
print(" 2.6 2.2000 1.9200 1.6400 1.4400 1.1000 0.8000 0.5200 0\n");
print(" \n");
print("
\n");
print(" \n\n");
}
if ($ac_injected) {
print(" \n");
print(" \n");
print(" velocities/mach\n");
print(" atmosphere/density-altitude\n");
print(" \n");
print(" 0 50000\n");
print(" 0.0 1.2000 1.2000\n");
print(" 1.0 1.2000 1.2000\n");
print(" \n");
print("
\n");
print(" \n\n");
}
print("\n");
}
//************************************************
//* MakeTurboprop() *
//************************************************
function MakeTurboprop() {
global $ac_enginename, $ac_enginepower,
$ac_augmented, $ac_injected;
// estimate thrust if given power
if(($ac_engineunits == 0) || ($ac_engineunits == 1)) {
$ac_enginepower *= 2.24;
}
print("\n");
printf(" %8.1f \n", $ac_enginepower);
print(" 0.0 \n");
print(" 0.55 \n");
print(" 0.03 \n");
print(" 30.0 \n");
print(" 60.0 \n");
print(" 100.0 \n");
print(" 100.0 \n");
print(" 0 \n");
print(" 0 \n\n");
print(" \n");
print(" \n");
print(" velocities/mach\n");
print(" atmosphere/density-altitude\n");
print(" \n");
print(" -10000 0 10000 20000 30000 40000 50000\n");
print(" 0.0 0.0430 0.0488 0.0528 0.0694 0.0899 0.1183 0.0\n");
print(" 0.2 0.0500 0.0501 0.0335 0.0544 0.0797 0.1049 0.0\n");
print(" 0.4 0.0040 0.0047 0.0020 0.0272 0.0595 0.0891 0.0\n");
print(" 0.6 0.0 0.0 0.0 0.0276 0.0718 0.0430 0.0\n");
print(" 0.8 0.0 0.0 0.0 0.0 0.0174 0.0086 0.0\n");
print(" 1.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0\n");
print(" \n");
print("
\n");
print(" \n\n");
print(" \n");
print(" \n");
print(" velocities/mach\n");
print(" atmosphere/density-altitude\n");
print(" \n");
print(" -10000 0 10000 20000 30000 40000 50000\n");
print(" 0.0 1.1260 1.0000 0.7400 0.5340 0.3720 0.2410 0.0\n");
print(" 0.2 1.1000 0.9340 0.6970 0.5060 0.3550 0.2310 0.0\n");
print(" 0.4 1.0000 0.6410 0.6120 0.4060 0.3570 0.2330 0.0\n");
print(" 0.6 0.4430 0.3510 0.2710 0.2020 0.1780 0.1020 0.0\n");
print(" 0.8 0.0240 0.0200 0.0160 0.0130 0.0110 0.0100 0.0\n");
print(" 1.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0\n");
print(" \n");
print("
\n");
print(" \n\n");
print("\n");
}
//************************************************
//* MakeRocket() *
//************************************************
function MakeRocket() {
global $ac_enginename, $ac_enginepower;
print("\n");
print(" 1.23 \n");
print(" 86556.00 \n");
print(" 0.10 \n");
print(" 0.67 \n");
print(" 1.00 \n");
print(" 0.40 \n");
print(" 91.50 \n");
print(" 105.20 \n");
print("\n");
}
?>