+#ifdef HAVE_CONFIG_H
+# include "config.h"
+#endif
+
#include <stdio.h>
#include <stdlib.h>
SGPropertyNode* fgGetNode (const char * path, bool create) { return 0; }
SGPropertyNode* fgGetNode (const char * path, int i, bool create) { return 0; }
float fgGetFloat (const char * name, float defaultValue) { return 0; }
-float fgGetDouble (const char * name, double defaultValue) { return 0; }
-float fgSetDouble (const char * name, double defaultValue) { return 0; }
+double fgGetDouble (const char * name, double defaultValue) { return 0; }
+bool fgSetDouble (const char * name, double defaultValue) { return false; }
static const float KTS2MPS = 0.514444444444;
static const float RPM2RAD = 0.10471975512;
readXML(argv[1], fdm);
} catch (const sg_exception &e) {
printf("XML parse error: %s (%s)\n",
- e.getFormattedMessage().c_str(), e.getOrigin().c_str());
+ e.getFormattedMessage().c_str(), e.getOrigin());
}
Airplane* airplane = fdm.getAirplane();
printf("Alt: %f\n", alt / FT2M);
printf("Spd: %f\n", speed / KTS2MPS);
+ printf("-----------------\n");
+ printf("Throt RPM thrustlbs HP eff %% torque\n");
for(int i=0; i<COUNT; i++) {
float throttle = i/(COUNT-1.0);
pe->setThrottle(throttle);
float eff = thrust * speed / power;
- printf("%6.3f: %6.1frpm %6.1flbs %6.1fhp %6.1f%% torque: %f\n",
+ printf("%5.3f %7.1f %8.1f %8.1f %7.1f %8.1f\n",
throttle, rpm, thrust * N2LB, power * (1/HP2W), 100*eff, eng->getTorque());
}
printf("\n");
printf("Propeller vs. RPM\n");
printf("-----------------\n");
+ printf("RPM thrustlbs HP eff %% torque\n");
for(int i=0; i<COUNT; i++) {
float thrust, torque, rpm = 3000 * i/(COUNT-1.0);
float omega = rpm * RPM2RAD;
speed, omega, &thrust, &torque);
float power = torque * omega;
float eff = (thrust * speed) / power;
- printf("%6.1frpm %6.1flbs %6.1fhp %.1f%% torque: %f\n",
+ printf("%7.1f %11.1f %10.1f %7.1f %11.1f\n",
rpm, thrust * N2LB, power * (1/HP2W), 100*eff, torque);
}
}