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