6 #include "PropEngine.hpp"
7 #include "Propeller.hpp"
8 #include "Atmosphere.hpp"
10 using namespace yasim;
12 // Usage: proptest plane.xml [alt-ft] [spd-ktas]
14 // Stubs. Not needed by a batch program, but required to link.
16 bool fgSetFloat (const char * name, float val) { return false; }
17 bool fgSetBool(char const * name, bool val) { return false; }
18 bool fgGetBool(char const * name, bool def) { return false; }
19 SGPropertyNode* fgGetNode (const char * path, bool create) { return 0; }
20 SGPropertyNode* fgGetNode (const char * path, int i, bool create) { return 0; }
21 float fgGetFloat (const char * name, float defaultValue) { return 0; }
22 float fgGetDouble (const char * name, double defaultValue) { return 0; }
23 float fgSetDouble (const char * name, double defaultValue) { return 0; }
25 static const float KTS2MPS = 0.514444444444;
26 static const float RPM2RAD = 0.10471975512;
27 static const float HP2W = 745.700;
28 static const float FT2M = 0.3048;
29 static const float N2LB = 0.224809;
31 // static const float DEG2RAD = 0.0174532925199;
32 // static const float LBS2N = 4.44822;
33 // static const float LBS2KG = 0.45359237;
34 // static const float KG2LBS = 2.2046225;
35 // static const float CM2GALS = 264.172037284;
36 // static const float INHG2PA = 3386.389;
37 // static const float K2DEGF = 1.8;
38 // static const float K2DEGFOFFSET = -459.4;
39 // static const float CIN2CM = 1.6387064e-5;
40 // static const float YASIM_PI = 3.14159265358979323846;
42 const int COUNT = 100;
44 int main(int argc, char** argv)
50 readXML(argv[1], fdm);
51 } catch (const sg_exception &e) {
52 printf("XML parse error: %s (%s)\n",
53 e.getFormattedMessage().c_str(), e.getOrigin().c_str());
56 Airplane* airplane = fdm.getAirplane();
57 PropEngine* pe = airplane->getThruster(0)->getPropEngine();
58 Propeller* prop = pe->getPropeller();
59 Engine* eng = pe->getEngine();
63 pe->setFuelState(true);
66 float alt = (argc > 2 ? atof(argv[2]) : 0) * FT2M;
67 pe->setAir(Atmosphere::getStdPressure(alt),
68 Atmosphere::getStdTemperature(alt),
69 Atmosphere::getStdDensity(alt));
71 float speed = (argc > 3 ? atof(argv[3]) : 0) * KTS2MPS;
73 wind[0] = -speed; wind[1] = wind[2] = 0;
76 printf("Alt: %f\n", alt / FT2M);
77 printf("Spd: %f\n", speed / KTS2MPS);
78 for(int i=0; i<COUNT; i++) {
79 float throttle = i/(COUNT-1.0);
80 pe->setThrottle(throttle);
83 float rpm = pe->getOmega() * (1/RPM2RAD);
87 float thrust = Math::mag3(tmp);
89 float power = pe->getOmega() * eng->getTorque();
91 float eff = thrust * speed / power;
93 printf("%6.3f: %6.1frpm %6.1flbs %6.1fhp %6.1f%% torque: %f\n",
94 throttle, rpm, thrust * N2LB, power * (1/HP2W), 100*eff, eng->getTorque());
98 printf("Propeller vs. RPM\n");
99 printf("-----------------\n");
100 for(int i=0; i<COUNT; i++) {
101 float thrust, torque, rpm = 3000 * i/(COUNT-1.0);
102 float omega = rpm * RPM2RAD;
103 prop->calc(Atmosphere::getStdDensity(alt),
104 speed, omega, &thrust, &torque);
105 float power = torque * omega;
106 float eff = (thrust * speed) / power;
107 printf("%6.1frpm %6.1flbs %6.1fhp %.1f%% torque: %f\n",
108 rpm, thrust * N2LB, power * (1/HP2W), 100*eff, torque);