_stall = 0;
_stallWidth = 0;
_stallPeak = 0;
+ _twist = 0;
_camber = 0;
_incidence = 0;
+ _inducedDrag = 1;
_dragScale = 1;
_liftRatio = 1;
_flap0Start = 0;
Wing::~Wing()
{
- for(int i=0; i<_surfs.size(); i++) {
+ int i;
+ for(i=0; i<_surfs.size(); i++) {
SurfRec* s = (SurfRec*)_surfs.get(i);
delete s->surface;
delete s;
void Wing::setBase(float* base)
{
- for(int i=0; i<3; i++) _base[i] = base[i];
+ int i;
+ for(i=0; i<3; i++) _base[i] = base[i];
}
void Wing::setLength(float length)
_stallPeak = fraction;
}
+void Wing::setTwist(float angle)
+{
+ _twist = angle;
+}
+
void Wing::setCamber(float camber)
{
_camber = camber;
void Wing::setIncidence(float incidence)
{
_incidence = incidence;
- for(int i=0; i<_surfs.size(); i++)
+ int i;
+ for(i=0; i<_surfs.size(); i++)
((SurfRec*)_surfs.get(i))->surface->setIncidence(incidence);
}
{
lval = Math::clamp(lval, -1, 1);
rval = Math::clamp(rval, -1, 1);
- for(int i=0; i<_flap0Surfs.size(); i++) {
+ int i;
+ for(i=0; i<_flap0Surfs.size(); i++) {
((Surface*)_flap0Surfs.get(i))->setFlap(lval);
if(_mirror) ((Surface*)_flap0Surfs.get(++i))->setFlap(rval);
}
{
lval = Math::clamp(lval, -1, 1);
rval = Math::clamp(rval, -1, 1);
- for(int i=0; i<_flap1Surfs.size(); i++) {
+ int i;
+ for(i=0; i<_flap1Surfs.size(); i++) {
((Surface*)_flap1Surfs.get(i))->setFlap(lval);
if(_mirror) ((Surface*)_flap1Surfs.get(++i))->setFlap(rval);
}
{
lval = Math::clamp(lval, 0, 1);
rval = Math::clamp(rval, 0, 1);
- for(int i=0; i<_spoilerSurfs.size(); i++) {
+ int i;
+ for(i=0; i<_spoilerSurfs.size(); i++) {
((Surface*)_spoilerSurfs.get(i))->setSpoiler(lval);
if(_mirror) ((Surface*)_spoilerSurfs.get(++i))->setSpoiler(rval);
}
void Wing::setSlat(float val)
{
val = Math::clamp(val, 0, 1);
- for(int i=0; i<_slatSurfs.size(); i++)
+ int i;
+ for(i=0; i<_slatSurfs.size(); i++)
((Surface*)_slatSurfs.get(i))->setSlat(val);
}
float Wing::getGroundEffect(float* posOut)
{
- for(int i=0; i<3; i++) posOut[i] = _base[i];
+ int i;
+ for(i=0; i<3; i++) posOut[i] = _base[i];
float span = _length * Math::cos(_sweep) * Math::cos(_dihedral);
span = 2*(span + Math::abs(_base[2]));
return span;
}
+void Wing::getTip(float* tip)
+{
+ tip[0] = -Math::tan(_sweep);
+ tip[1] = Math::cos(_dihedral);
+ tip[2] = Math::sin(_dihedral);
+ Math::unit3(tip, tip);
+ Math::mul3(_length, tip, tip);
+ Math::add3(_base, tip, tip);
+}
+
+bool Wing::isMirrored()
+{
+ return _mirror;
+}
+
void Wing::compile()
{
// Have we already been compiled?
bounds[6] = _slatStart; bounds[7] = _slatEnd;
// Sort in increasing order
- for(int i=0; i<8; i++) {
+ int i;
+ for(i=0; i<8; i++) {
int minIdx = i;
float minVal = bounds[i];
- for(int j=i+1; j<8; j++) {
+ int j;
+ for(j=i+1; j<8; j++) {
if(bounds[j] < minVal) {
minIdx = j;
minVal = bounds[j];
// Uniqify
float last = bounds[0];
int nbounds = 1;
- for(int i=1; i<8; i++) {
+ for(i=1; i<8; i++) {
if(bounds[i] != last)
bounds[nbounds++] = bounds[i];
last = bounds[i];
// Calculate a "nominal" segment length equal to an average chord,
// normalized to lie within 0-1 over the length of the wing.
- float segLen = _chord * (0.5*(_taper+1)) / _length;
+ float segLen = _chord * (0.5f*(_taper+1)) / _length;
// Generating a unit vector pointing out the left wing.
float left[3];
if(_mirror) {
// Derive the right side orientation matrix from this one.
- for(int i=0; i<9; i++) rightOrient[i] = orient[i];
+ int i;
+ for(i=0; i<9; i++) rightOrient[i] = orient[i];
// Negate all Y coordinates, this gets us a valid basis, but
// it's left handed! So...
- for(int i=1; i<9; i+=3) rightOrient[i] = -rightOrient[i];
+ for(i=1; i<9; i+=3) rightOrient[i] = -rightOrient[i];
// Change the direction of the Y axis to get back to a
// right-handed system.
- for(int i=3; i<6; i++) rightOrient[i] = -rightOrient[i];
+ for(i=3; i<6; i++) rightOrient[i] = -rightOrient[i];
}
// Now go through each boundary and make segments
- for(int i=0; i<(nbounds-1); i++) {
+ for(i=0; i<(nbounds-1); i++) {
float start = bounds[i];
float end = bounds[i+1];
float mid = (start+end)/2;
// and flap1 are set. Right now flap1 overrides.
int nSegs = (int)Math::ceil((end-start)/segLen);
+ if (_twist != 0 && nSegs < 8) // more segments if twisted
+ nSegs = 8;
float segWid = _length * (end - start)/nSegs;
- for(int j=0; j<nSegs; j++) {
- float frac = start + (j+0.5) * (end-start)/nSegs;
+ int j;
+ for(j=0; j<nSegs; j++) {
+ float frac = start + (j+0.5f) * (end-start)/nSegs;
float pos[3];
interp(root, tip, frac, pos);
sr->surface = s;
sr->weight = chord * segWid;
s->setTotalDrag(sr->weight);
+ s->setTwist(_twist * frac);
_surfs.add(sr);
if(_mirror) {
sr->surface = s;
sr->weight = chord * segWid;
s->setTotalDrag(sr->weight);
+ s->setTwist(_twist * Math::sqrt(frac));
_surfs.add(sr);
}
}
}
+
+ // Last of all, re-set the incidence in case setIncidence() was
+ // called before we were compiled.
+ setIncidence(_incidence);
}
float Wing::getDragScale()
void Wing::setDragScale(float scale)
{
_dragScale = scale;
- for(int i=0; i<_surfs.size(); i++) {
+ int i;
+ for(i=0; i<_surfs.size(); i++) {
SurfRec* s = (SurfRec*)_surfs.get(i);
s->surface->setTotalDrag(scale * s->weight);
}
void Wing::setLiftRatio(float ratio)
{
_liftRatio = ratio;
- for(int i=0; i<_surfs.size(); i++)
+ int i;
+ for(i=0; i<_surfs.size(); i++)
((SurfRec*)_surfs.get(i))->surface->setZDrag(ratio);
}
// The negative AoA stall is the same if we're using an uncambered
// airfoil, otherwise a "little badder".
if(_camber > 0) {
- s->setStall(1, stallAoA * 0.8);
- s->setStallWidth(1, _stallWidth * 0.5);
+ s->setStall(1, stallAoA * 0.8f);
+ s->setStallWidth(1, _stallWidth * 0.5f);
} else {
s->setStall(1, stallAoA);
s->setStall(1, _stallWidth);
// The "reverse" stalls are unmeasurable junk. Just use 13deg and
// "sharp".
s->setStallPeak(1, 1);
- for(int i=2; i<4; i++) {
- s->setStall(i, 0.2267);
+ int i;
+ for(i=2; i<4; i++) {
+ s->setStall(i, 0.2267f);
s->setStallWidth(i, 1);
}
if(slat) _slatSurfs.add(s);
if(spoiler) _spoilerSurfs.add(s);
+ s->setInducedDrag(_inducedDrag);
+
return s;
}
projects / flightgear.git / blobdiff