3ef1c6f540
properly correcting for the gear ratio. This is the source of the problems Vivian and Jim were having with the Spitfire and Mustang.
110 lines
3.5 KiB
C++
110 lines
3.5 KiB
C++
#include <stdio.h>
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#include <stdlib.h>
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#include "Math.hpp"
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#include "FGFDM.hpp"
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#include "PropEngine.hpp"
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#include "Propeller.hpp"
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#include "Atmosphere.hpp"
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using namespace yasim;
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// Usage: proptest plane.xml [alt-ft] [spd-ktas]
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// Stubs. Not needed by a batch program, but required to link.
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class SGPropertyNode;
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bool fgSetFloat (const char * name, float val) { return false; }
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bool fgSetBool(char const * name, bool val) { return false; }
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bool fgGetBool(char const * name, bool def) { return false; }
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SGPropertyNode* fgGetNode (const char * path, bool create) { return 0; }
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SGPropertyNode* fgGetNode (const char * path, int i, bool create) { return 0; }
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float fgGetFloat (const char * name, float defaultValue) { return 0; }
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float fgGetDouble (const char * name, double defaultValue) { return 0; }
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float fgSetDouble (const char * name, double defaultValue) { return 0; }
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static const float KTS2MPS = 0.514444444444;
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static const float RPM2RAD = 0.10471975512;
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static const float HP2W = 745.700;
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static const float FT2M = 0.3048;
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static const float N2LB = 0.224809;
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// static const float DEG2RAD = 0.0174532925199;
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// static const float LBS2N = 4.44822;
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// static const float LBS2KG = 0.45359237;
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// static const float KG2LBS = 2.2046225;
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// static const float CM2GALS = 264.172037284;
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// static const float INHG2PA = 3386.389;
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// static const float K2DEGF = 1.8;
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// static const float K2DEGFOFFSET = -459.4;
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// static const float CIN2CM = 1.6387064e-5;
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// static const float YASIM_PI = 3.14159265358979323846;
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const int COUNT = 100;
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int main(int argc, char** argv)
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{
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FGFDM fdm;
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// Read
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try {
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readXML(argv[1], fdm);
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} catch (const sg_exception &e) {
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printf("XML parse error: %s (%s)\n",
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e.getFormattedMessage().c_str(), e.getOrigin().c_str());
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}
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Airplane* airplane = fdm.getAirplane();
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PropEngine* pe = airplane->getThruster(0)->getPropEngine();
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Propeller* prop = pe->getPropeller();
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Engine* eng = pe->getEngine();
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pe->init();
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pe->setMixture(1);
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pe->setFuelState(true);
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eng->setBoost(1);
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float alt = (argc > 2 ? atof(argv[2]) : 0) * FT2M;
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pe->setAir(Atmosphere::getStdPressure(alt),
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Atmosphere::getStdTemperature(alt),
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Atmosphere::getStdDensity(alt));
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float speed = (argc > 3 ? atof(argv[3]) : 0) * KTS2MPS;
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float wind[3];
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wind[0] = -speed; wind[1] = wind[2] = 0;
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pe->setWind(wind);
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printf("Alt: %f\n", alt / FT2M);
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printf("Spd: %f\n", speed / KTS2MPS);
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for(int i=0; i<COUNT; i++) {
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float throttle = i/(COUNT-1.0);
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pe->setThrottle(throttle);
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pe->stabilize();
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float rpm = pe->getOmega() * (1/RPM2RAD);
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float tmp[3];
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pe->getThrust(tmp);
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float thrust = Math::mag3(tmp);
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float power = pe->getOmega() * eng->getTorque();
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float eff = thrust * speed / power;
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printf("%6.3f: %6.1frpm %6.1flbs %6.1fhp %6.1f%% torque: %f\n",
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throttle, rpm, thrust * N2LB, power * (1/HP2W), 100*eff, eng->getTorque());
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}
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printf("\n");
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printf("Propeller vs. RPM\n");
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printf("-----------------\n");
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for(int i=0; i<COUNT; i++) {
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float thrust, torque, rpm = 3000 * i/(COUNT-1.0);
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float omega = rpm * RPM2RAD;
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prop->calc(Atmosphere::getStdDensity(alt),
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speed, omega, &thrust, &torque);
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float power = torque * omega;
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float eff = (thrust * speed) / power;
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printf("%6.1frpm %6.1flbs %6.1fhp %.1f%% torque: %f\n",
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rpm, thrust * N2LB, power * (1/HP2W), 100*eff, torque);
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}
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}
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