448 lines
11 KiB
C++
448 lines
11 KiB
C++
#include "Math.hpp"
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#include "Surface.hpp"
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#include "Wing.hpp"
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namespace yasim {
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Wing::Wing()
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{
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_mirror = false;
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_base[0] = _base[1] = _base[2] = 0;
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_length = 0;
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_chord = 0;
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_taper = 0;
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_sweep = 0;
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_dihedral = 0;
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_stall = 0;
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_stallWidth = 0;
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_stallPeak = 0;
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_camber = 0;
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_incidence = 0;
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_dragScale = 1;
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_liftRatio = 1;
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_flap0Start = 0;
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_flap0End = 0;
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_flap0Lift = 0;
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_flap0Drag = 0;
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_flap1Start = 0;
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_flap1End = 0;
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_flap1Lift = 0;
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_flap1Drag = 0;
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_spoilerStart = 0;
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_spoilerEnd = 0;
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_spoilerLift = 0;
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_spoilerDrag = 0;
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_slatStart = 0;
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_slatEnd = 0;
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_slatAoA = 0;
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_slatDrag = 0;
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}
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Wing::~Wing()
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{
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int i;
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for(i=0; i<_surfs.size(); i++) {
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SurfRec* s = (SurfRec*)_surfs.get(i);
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delete s->surface;
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delete s;
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}
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}
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int Wing::numSurfaces()
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{
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return _surfs.size();
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}
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Surface* Wing::getSurface(int n)
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{
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return ((SurfRec*)_surfs.get(n))->surface;
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}
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float Wing::getSurfaceWeight(int n)
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{
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return ((SurfRec*)_surfs.get(n))->weight;
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}
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void Wing::setMirror(bool mirror)
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{
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_mirror = mirror;
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}
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void Wing::setBase(float* base)
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{
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int i;
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for(i=0; i<3; i++) _base[i] = base[i];
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}
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void Wing::setLength(float length)
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{
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_length = length;
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}
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void Wing::setChord(float chord)
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{
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_chord = chord;
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}
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void Wing::setTaper(float taper)
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{
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_taper = taper;
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}
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void Wing::setSweep(float sweep)
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{
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_sweep = sweep;
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}
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void Wing::setDihedral(float dihedral)
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{
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_dihedral = dihedral;
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}
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void Wing::setStall(float aoa)
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{
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_stall = aoa;
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}
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void Wing::setStallWidth(float angle)
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{
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_stallWidth = angle;
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}
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void Wing::setStallPeak(float fraction)
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{
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_stallPeak = fraction;
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}
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void Wing::setCamber(float camber)
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{
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_camber = camber;
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}
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void Wing::setIncidence(float incidence)
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{
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_incidence = incidence;
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int i;
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for(i=0; i<_surfs.size(); i++)
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((SurfRec*)_surfs.get(i))->surface->setIncidence(incidence);
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}
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void Wing::setFlap0(float start, float end, float lift, float drag)
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{
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_flap0Start = start;
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_flap0End = end;
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_flap0Lift = lift;
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_flap0Drag = drag;
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}
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void Wing::setFlap1(float start, float end, float lift, float drag)
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{
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_flap1Start = start;
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_flap1End = end;
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_flap1Lift = lift;
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_flap1Drag = drag;
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}
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void Wing::setSlat(float start, float end, float aoa, float drag)
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{
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_slatStart = start;
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_slatEnd = end;
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_slatAoA = aoa;
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_slatDrag = drag;
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}
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void Wing::setSpoiler(float start, float end, float lift, float drag)
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{
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_spoilerStart = start;
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_spoilerEnd = end;
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_spoilerLift = lift;
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_spoilerDrag = drag;
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}
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void Wing::setFlap0(float lval, float rval)
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{
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lval = Math::clamp(lval, -1, 1);
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rval = Math::clamp(rval, -1, 1);
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int i;
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for(i=0; i<_flap0Surfs.size(); i++) {
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((Surface*)_flap0Surfs.get(i))->setFlap(lval);
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if(_mirror) ((Surface*)_flap0Surfs.get(++i))->setFlap(rval);
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}
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}
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void Wing::setFlap1(float lval, float rval)
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{
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lval = Math::clamp(lval, -1, 1);
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rval = Math::clamp(rval, -1, 1);
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int i;
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for(i=0; i<_flap1Surfs.size(); i++) {
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((Surface*)_flap1Surfs.get(i))->setFlap(lval);
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if(_mirror) ((Surface*)_flap1Surfs.get(++i))->setFlap(rval);
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}
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}
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void Wing::setSpoiler(float lval, float rval)
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{
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lval = Math::clamp(lval, 0, 1);
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rval = Math::clamp(rval, 0, 1);
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int i;
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for(i=0; i<_spoilerSurfs.size(); i++) {
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((Surface*)_spoilerSurfs.get(i))->setSpoiler(lval);
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if(_mirror) ((Surface*)_spoilerSurfs.get(++i))->setSpoiler(rval);
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}
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}
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void Wing::setSlat(float val)
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{
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val = Math::clamp(val, 0, 1);
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int i;
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for(i=0; i<_slatSurfs.size(); i++)
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((Surface*)_slatSurfs.get(i))->setSlat(val);
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}
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float Wing::getGroundEffect(float* posOut)
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{
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int i;
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for(i=0; i<3; i++) posOut[i] = _base[i];
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float span = _length * Math::cos(_sweep) * Math::cos(_dihedral);
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span = 2*(span + Math::abs(_base[2]));
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return span;
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}
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void Wing::getTip(float* tip)
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{
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tip[0] = -Math::tan(_sweep);
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tip[1] = Math::cos(_dihedral);
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tip[2] = Math::sin(_dihedral);
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Math::unit3(tip, tip);
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Math::mul3(_length, tip, tip);
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Math::add3(_base, tip, tip);
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}
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bool Wing::isMirrored()
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{
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return _mirror;
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}
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void Wing::compile()
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{
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// Have we already been compiled?
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if(_surfs.size() != 0) return;
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// Assemble the start/end coordinates into an array, sort them,
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// and remove duplicates. This gives us the boundaries of our
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// segments.
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float bounds[8];
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bounds[0] = _flap0Start; bounds[1] = _flap0End;
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bounds[2] = _flap1Start; bounds[3] = _flap1End;
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bounds[4] = _spoilerStart; bounds[5] = _spoilerEnd;
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bounds[6] = _slatStart; bounds[7] = _slatEnd;
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// Sort in increasing order
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int i;
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for(i=0; i<8; i++) {
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int minIdx = i;
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float minVal = bounds[i];
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int j;
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for(j=i+1; j<8; j++) {
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if(bounds[j] < minVal) {
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minIdx = j;
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minVal = bounds[j];
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}
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}
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float tmp = bounds[i];
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bounds[i] = minVal; bounds[minIdx] = tmp;
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}
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// Uniqify
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float last = bounds[0];
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int nbounds = 1;
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for(i=1; i<8; i++) {
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if(bounds[i] != last)
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bounds[nbounds++] = bounds[i];
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last = bounds[i];
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}
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// Calculate a "nominal" segment length equal to an average chord,
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// normalized to lie within 0-1 over the length of the wing.
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float segLen = _chord * (0.5f*(_taper+1)) / _length;
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// Generating a unit vector pointing out the left wing.
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float left[3];
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left[0] = -Math::tan(_sweep);
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left[1] = Math::cos(_dihedral);
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left[2] = Math::sin(_dihedral);
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Math::unit3(left, left);
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// Calculate coordinates for the root and tip of the wing
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float root[3], tip[3];
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Math::set3(_base, root);
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Math::set3(left, tip);
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Math::mul3(_length, tip, tip);
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Math::add3(root, tip, tip);
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// The wing's Y axis will be the "left" vector. The Z axis will
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// be perpendicular to this and the local (!) X axis, because we
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// want motion along the local X axis to be zero AoA (i.e. in the
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// wing's XY plane) by definition. Then the local X coordinate is
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// just Y cross Z.
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float orient[9], rightOrient[9];
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float *x = orient, *y = orient+3, *z = orient+6;
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x[0] = 1; x[1] = 0; x[2] = 0;
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Math::set3(left, y);
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Math::cross3(x, y, z);
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Math::unit3(z, z);
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Math::cross3(y, z, x);
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if(_mirror) {
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// Derive the right side orientation matrix from this one.
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int i;
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for(i=0; i<9; i++) rightOrient[i] = orient[i];
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// Negate all Y coordinates, this gets us a valid basis, but
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// it's left handed! So...
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for(i=1; i<9; i+=3) rightOrient[i] = -rightOrient[i];
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// Change the direction of the Y axis to get back to a
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// right-handed system.
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for(i=3; i<6; i++) rightOrient[i] = -rightOrient[i];
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}
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// Now go through each boundary and make segments
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for(i=0; i<(nbounds-1); i++) {
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float start = bounds[i];
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float end = bounds[i+1];
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float mid = (start+end)/2;
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bool flap0=0, flap1=0, slat=0, spoiler=0;
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if(_flap0Start < mid && mid < _flap0End) flap0 = 1;
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if(_flap1Start < mid && mid < _flap1End) flap1 = 1;
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if(_slatStart < mid && mid < _slatEnd) slat = 1;
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if(_spoilerStart < mid && mid < _spoilerEnd) spoiler = 1;
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// FIXME: Should probably detect an error here if both flap0
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// and flap1 are set. Right now flap1 overrides.
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int nSegs = (int)Math::ceil((end-start)/segLen);
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float segWid = _length * (end - start)/nSegs;
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int j;
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for(j=0; j<nSegs; j++) {
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float frac = start + (j+0.5f) * (end-start)/nSegs;
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float pos[3];
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interp(root, tip, frac, pos);
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float chord = _chord * (1 - (1-_taper)*frac);
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Surface *s = newSurface(pos, orient, chord,
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flap0, flap1, slat, spoiler);
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SurfRec *sr = new SurfRec();
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sr->surface = s;
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sr->weight = chord * segWid;
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s->setTotalDrag(sr->weight);
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_surfs.add(sr);
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if(_mirror) {
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pos[1] = -pos[1];
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s = newSurface(pos, rightOrient, chord,
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flap0, flap1, slat, spoiler);
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sr = new SurfRec();
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sr->surface = s;
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sr->weight = chord * segWid;
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s->setTotalDrag(sr->weight);
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_surfs.add(sr);
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}
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}
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}
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// Last of all, re-set the incidence in case setIncidence() was
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// called before we were compiled.
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setIncidence(_incidence);
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}
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float Wing::getDragScale()
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{
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return _dragScale;
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}
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void Wing::setDragScale(float scale)
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{
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_dragScale = scale;
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int i;
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for(i=0; i<_surfs.size(); i++) {
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SurfRec* s = (SurfRec*)_surfs.get(i);
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s->surface->setTotalDrag(scale * s->weight);
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}
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}
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void Wing::setLiftRatio(float ratio)
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{
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_liftRatio = ratio;
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int i;
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for(i=0; i<_surfs.size(); i++)
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((SurfRec*)_surfs.get(i))->surface->setZDrag(ratio);
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}
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float Wing::getLiftRatio()
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{
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return _liftRatio;
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}
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Surface* Wing::newSurface(float* pos, float* orient, float chord,
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bool flap0, bool flap1, bool slat, bool spoiler)
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{
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Surface* s = new Surface();
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s->setPosition(pos);
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s->setOrientation(orient);
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s->setChord(chord);
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// Camber is expressed as a fraction of stall peak, so convert.
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s->setBaseZDrag(_camber*_stallPeak);
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// The "main" (i.e. normal) stall angle
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float stallAoA = _stall - _stallWidth/4;
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s->setStall(0, stallAoA);
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s->setStallWidth(0, _stallWidth);
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s->setStallPeak(0, _stallPeak);
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// The negative AoA stall is the same if we're using an uncambered
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// airfoil, otherwise a "little badder".
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if(_camber > 0) {
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s->setStall(1, stallAoA * 0.8f);
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s->setStallWidth(1, _stallWidth * 0.5f);
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} else {
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s->setStall(1, stallAoA);
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s->setStall(1, _stallWidth);
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}
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// The "reverse" stalls are unmeasurable junk. Just use 13deg and
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// "sharp".
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s->setStallPeak(1, 1);
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int i;
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for(i=2; i<4; i++) {
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s->setStall(i, 0.2267f);
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s->setStallWidth(i, 1);
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}
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if(flap0) s->setFlapParams(_flap0Lift, _flap0Drag);
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if(flap1) s->setFlapParams(_flap1Lift, _flap1Drag);
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if(slat) s->setSlatParams(_slatAoA, _slatDrag);
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if(spoiler) s->setSpoilerParams(_spoilerLift, _spoilerDrag);
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if(flap0) _flap0Surfs.add(s);
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if(flap1) _flap1Surfs.add(s);
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if(slat) _slatSurfs.add(s);
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if(spoiler) _spoilerSurfs.add(s);
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return s;
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}
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void Wing::interp(float* v1, float* v2, float frac, float* out)
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{
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out[0] = v1[0] + frac*(v2[0]-v1[0]);
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out[1] = v1[1] + frac*(v2[1]-v1[1]);
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out[2] = v1[2] + frac*(v2[2]-v1[2]);
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}
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}; // namespace yasim
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