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 bool fgSetString(char const * name, char const * str) { return false; }
20 SGPropertyNode* fgGetNode (const char * path, bool create) { return 0; }
21 SGPropertyNode* fgGetNode (const char * path, int i, bool create) { return 0; }
22 float fgGetFloat (const char * name, float defaultValue) { return 0; }
23 float fgGetDouble (const char * name, double defaultValue) { return 0; }
24 float fgSetDouble (const char * name, double defaultValue) { return 0; }
26 static const float KTS2MPS = 0.514444444444;
27 static const float RPM2RAD = 0.10471975512;
28 static const float HP2W = 745.700;
29 static const float FT2M = 0.3048;
30 static const float N2LB = 0.224809;
32 // static const float DEG2RAD = 0.0174532925199;
33 // static const float LBS2N = 4.44822;
34 // static const float LBS2KG = 0.45359237;
35 // static const float KG2LBS = 2.2046225;
36 // static const float CM2GALS = 264.172037284;
37 // static const float INHG2PA = 3386.389;
38 // static const float K2DEGF = 1.8;
39 // static const float K2DEGFOFFSET = -459.4;
40 // static const float CIN2CM = 1.6387064e-5;
41 // static const float YASIM_PI = 3.14159265358979323846;
43 const int COUNT = 100;
45 int main(int argc, char** argv)
51 readXML(argv[1], fdm);
52 } catch (const sg_exception &e) {
53 printf("XML parse error: %s (%s)\n",
54 e.getFormattedMessage().c_str(), e.getOrigin().c_str());
57 Airplane* airplane = fdm.getAirplane();
58 PropEngine* pe = airplane->getThruster(0)->getPropEngine();
59 Propeller* prop = pe->getPropeller();
60 Engine* eng = pe->getEngine();
64 pe->setFuelState(true);
67 float alt = (argc > 2 ? atof(argv[2]) : 0) * FT2M;
68 pe->setAir(Atmosphere::getStdPressure(alt),
69 Atmosphere::getStdTemperature(alt),
70 Atmosphere::getStdDensity(alt));
72 float speed = (argc > 3 ? atof(argv[3]) : 0) * KTS2MPS;
74 wind[0] = -speed; wind[1] = wind[2] = 0;
77 printf("Alt: %f\n", alt / FT2M);
78 printf("Spd: %f\n", speed / KTS2MPS);
79 for(int i=0; i<COUNT; i++) {
80 float throttle = i/(COUNT-1.0);
81 pe->setThrottle(throttle);
84 float rpm = pe->getOmega() * (1/RPM2RAD);
88 float thrust = Math::mag3(tmp);
90 float power = pe->getOmega() * eng->getTorque();
92 float eff = thrust * speed / power;
94 printf("%6.3f: %6.1frpm %6.1flbs %6.1fhp %6.1f%% torque: %f\n",
95 throttle, rpm, thrust * N2LB, power * (1/HP2W), 100*eff, eng->getTorque());
99 printf("Propeller vs. RPM\n");
100 printf("-----------------\n");
101 for(int i=0; i<COUNT; i++) {
102 float thrust, torque, rpm = 3000 * i/(COUNT-1.0);
103 float omega = rpm * RPM2RAD;
104 prop->calc(Atmosphere::getStdDensity(alt),
105 speed, omega, &thrust, &torque);
106 float power = torque * omega;
107 float eff = (thrust * speed) / power;
108 printf("%6.1frpm %6.1flbs %6.1fhp %.1f%% torque: %f\n",
109 rpm, thrust * N2LB, power * (1/HP2W), 100*eff, torque);