From 5f78545961aa73393e143cf216ca4de1544f827f Mon Sep 17 00:00:00 2001 From: Henning Stahlke Date: Sun, 19 Feb 2017 12:57:39 +0100 Subject: [PATCH] only white spaces --- src/FDM/YASim/yasim-test.cpp | 182 +++++++++++++++++------------------ 1 file changed, 91 insertions(+), 91 deletions(-) diff --git a/src/FDM/YASim/yasim-test.cpp b/src/FDM/YASim/yasim-test.cpp index 312774006..3d3193854 100644 --- a/src/FDM/YASim/yasim-test.cpp +++ b/src/FDM/YASim/yasim-test.cpp @@ -33,9 +33,9 @@ static const float KTS2MPS = 0.514444444444; enum Config { - CONFIG_NONE, - CONFIG_APPROACH, - CONFIG_CRUISE, + CONFIG_NONE, + CONFIG_APPROACH, + CONFIG_CRUISE, }; // Generate a graph of lift, drag and L/D against AoA at the specified @@ -50,70 +50,70 @@ enum Config */ void yasim_graph(Airplane* a, float alt, float kts, int cfg = CONFIG_NONE) { - Model* m = a->getModel(); - State s; - - m->setAir(Atmosphere::getStdPressure(alt), - Atmosphere::getStdTemperature(alt), - Atmosphere::getStdDensity(alt)); + Model* m = a->getModel(); + State s; - switch (cfg) { - case CONFIG_APPROACH: - a->loadApproachControls(); - break; - case CONFIG_CRUISE: - a->loadCruiseControls(); - break; - case CONFIG_NONE: - break; - } - //if we fake the properties we could also use FGFDM::getExternalInput() + m->setAir(Atmosphere::getStdPressure(alt), + Atmosphere::getStdTemperature(alt), + Atmosphere::getStdDensity(alt)); + + switch (cfg) { + case CONFIG_APPROACH: + a->loadApproachControls(); + break; + case CONFIG_CRUISE: + a->loadCruiseControls(); + break; + case CONFIG_NONE: + break; + } + //if we fake the properties we could also use FGFDM::getExternalInput() - m->getBody()->recalc(); + m->getBody()->recalc(); - for(int deg=-179; deg<=179; deg++) { - float aoa = deg * DEG2RAD; - Airplane::setupState(aoa, kts * KTS2MPS, 0 ,&s); - m->getBody()->reset(); - m->initIteration(); - m->calcForces(&s); + for(int deg=-179; deg<=179; deg++) { + float aoa = deg * DEG2RAD; + Airplane::setupState(aoa, kts * KTS2MPS, 0 ,&s); + m->getBody()->reset(); + m->initIteration(); + m->calcForces(&s); - float acc[3]; - m->getBody()->getAccel(acc); - Math::tmul33(s.orient, acc, acc); + float acc[3]; + m->getBody()->getAccel(acc); + Math::tmul33(s.orient, acc, acc); - float drag = acc[0] * (-1/9.8); - float lift = 1 + acc[2] * (1/9.8); + float drag = acc[0] * (-1/9.8); + float lift = 1 + acc[2] * (1/9.8); - printf("%d %g %g %g\n", deg, lift, drag, lift/drag); - } + printf("%d %g %g %g\n", deg, lift, drag, lift/drag); + } } void yasim_masses(Airplane* a) { - RigidBody* body = a->getModel()->getBody(); - int i, N = body->numMasses(); - float pos[3]; - float m, mass = 0; - printf("id posx posy posz mass\n"); - for (i = 0; i < N; i++) - { - body->getMassPosition(i, pos); - m = body->getMass(i); - printf("%d %.3f %.3f %.3f %.3f\n", i, pos[0], pos[1], pos[2], m); - mass += m; - } - printf("Total mass: %g", mass); + RigidBody* body = a->getModel()->getBody(); + int i, N = body->numMasses(); + float pos[3]; + float m, mass = 0; + printf("id posx posy posz mass\n"); + for (i = 0; i < N; i++) + { + body->getMassPosition(i, pos); + m = body->getMass(i); + printf("%d %.3f %.3f %.3f %.3f\n", i, pos[0], pos[1], pos[2], m); + mass += m; + } + printf("Total mass: %g", mass); } int usage() { - fprintf(stderr, "Usage: yasim [-g [-a alt] [-s kts] [-approach | -cruise] ]\n"); - fprintf(stderr, " yasim [-m]\n"); - fprintf(stderr, " -g print lift/drag table: aoa, lift, drag, lift/drag \n"); - fprintf(stderr, " -m print mass distribution table: id, x, y, z, mass \n"); - return 1; + fprintf(stderr, "Usage: yasim [-g [-a alt] [-s kts] [-approach | -cruise] ]\n"); + fprintf(stderr, " yasim [-m]\n"); + fprintf(stderr, " -g print lift/drag table: aoa, lift, drag, lift/drag \n"); + fprintf(stderr, " -m print mass distribution table: id, x, y, z, mass \n"); + return 1; } @@ -137,50 +137,50 @@ int main(int argc, char** argv) if(a->getFailureMsg()) printf("SOLUTION FAILURE: %s\n", a->getFailureMsg()); if(!a->getFailureMsg() && argc > 2 ) { - if(strcmp(argv[2], "-g") == 0) { - float alt = 5000, kts = 100; - int cfg = CONFIG_NONE; - for(int i=3; igetCruiseAoA() * RAD2DEG; - float tail = -1 * a->getTailIncidence() * RAD2DEG; - float drag = 1000 * a->getDragCoefficient(); - float cg[3]; - a->getModel()->getBody()->getCG(cg); - a->getModel()->getBody()->recalc(); + else if(std::strcmp(argv[i], "-approach") == 0) cfg = CONFIG_APPROACH; + else if(std::strcmp(argv[i], "-cruise") == 0) cfg = CONFIG_CRUISE; + else return usage(); + } + yasim_graph(a, alt, kts, cfg); + } + else if(strcmp(argv[2], "-m") == 0) { + yasim_masses(a); + } + } + else { + printf("Solution results:"); + float aoa = a->getCruiseAoA() * RAD2DEG; + float tail = -1 * a->getTailIncidence() * RAD2DEG; + float drag = 1000 * a->getDragCoefficient(); + float cg[3]; + a->getModel()->getBody()->getCG(cg); + a->getModel()->getBody()->recalc(); - float SI_inertia[9]; - a->getModel()->getBody()->getInertiaMatrix(SI_inertia); - - printf(" Iterations: %d\n", a->getSolutionIterations()); - printf(" Drag Coefficient: %f\n", drag); - printf(" Lift Ratio: %f\n", a->getLiftRatio()); - printf(" Cruise AoA: %f\n", aoa); - printf(" Tail Incidence: %f\n", tail); - printf("Approach Elevator: %f\n", a->getApproachElevator()); - printf(" CG: x:%.3f, y:%.3f, z:%.3f\n\n", cg[0], cg[1], cg[2]); - printf("Inertia tensor [kg*m^2], origo at CG:\n"); - printf(" %7.3f, %7.3f, %7.3f\n", SI_inertia[0], SI_inertia[1], SI_inertia[2]); - printf(" %7.3f, %7.3f, %7.3f\n", SI_inertia[3], SI_inertia[4], SI_inertia[5]); - printf(" %7.3f, %7.3f, %7.3f\n", SI_inertia[6], SI_inertia[7], SI_inertia[8]); - } + float SI_inertia[9]; + a->getModel()->getBody()->getInertiaMatrix(SI_inertia); + + printf(" Iterations: %d\n", a->getSolutionIterations()); + printf(" Drag Coefficient: %f\n", drag); + printf(" Lift Ratio: %f\n", a->getLiftRatio()); + printf(" Cruise AoA: %f\n", aoa); + printf(" Tail Incidence: %f\n", tail); + printf("Approach Elevator: %f\n", a->getApproachElevator()); + printf(" CG: x:%.3f, y:%.3f, z:%.3f\n\n", cg[0], cg[1], cg[2]); + printf("Inertia tensor [kg*m^2], origo at CG:\n"); + printf(" %7.3f, %7.3f, %7.3f\n", SI_inertia[0], SI_inertia[1], SI_inertia[2]); + printf(" %7.3f, %7.3f, %7.3f\n", SI_inertia[3], SI_inertia[4], SI_inertia[5]); + printf(" %7.3f, %7.3f, %7.3f\n", SI_inertia[6], SI_inertia[7], SI_inertia[8]); + } delete fdm; return 0; }