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