Does the Sea King I redid load?
Me either. I just tried again on a "ultra clean" installation, no add-ons at all except the Dauphin (not even sound). I'm stumped.
weird. Reduced the RSC. If I just apply hover then then ceiling is around 4500. Not sure why the meshes are not showing up?
You should only get Hover and rotors if K is pressed.
Kev has a mod on OH that's supposed to fix some of his vessels going invisible.
Kind regards,
NT
With that version and full vertical thrust I reach about 4200m altitude and then fall down (still full thrust) to 170m. Raising slowly I reach the point where thrust equals gravity at 2500m.
For the horizontal speed I easily got 1400m/s at an altitude of 500m. Then I had to reduce pitch manually so higher speed could be reached slower.
SetRotDrag (_V(1.5,1.5,1.5));
//Airfoils
CreateAirfoil3(LIFT_VERTICAL,_V(0,0,-0.5),VLiftCoeff,0,0,1,1);
CreateAirfoil3(LIFT_HORIZONTAL,_V(0,0,-4),HLiftCoeff,0,0,1,1);
Which number value is the drag in the airfoils?
//vertical lift component (wings and body)
void VLiftCoeff(VESSEL *v,double aoa,double M,double Re,void *context,double *cl,double *cm,double *cd)
{
int i;
const int nabsc=9;
static const double AOA[nabsc]={-180*RAD,-60*RAD,-30*RAD, -2*RAD, 15*RAD,20*RAD,25*RAD,60*RAD,180*RAD};
static const double CL[nabsc] ={ 0, 0, -0.4, 0, 0.7, 1, 0.8, 0, 0};
static const double CM[nabsc] ={ 0, 0, 0.014, 0.0039, -0.006,-0.008,-0.010, 0, 0};
for(i=0;i<nabsc-1 && AOA[i+1]<aoa;i++);
double f=(aoa-AOA[i])/(AOA[i+1]-AOA[i]);
*cl=CL[i]+(CL[i+1]-CL[i])*f; //aoa-dependent lift coefficient
*cm=CM[i]+(CM[i+1]-CM[i])*f; //aoa-dependent moment coefficient
double saoa=sin(aoa);
double pd=0.015+0.4*saoa*saoa; //profile drag
*cd=pd+oapiGetInducedDrag(*cl,1.5,0.7)+oapiGetWaveDrag(M,0.75,1.0,1.1,0.04);
//profile drag+(lift-)induced drag+transonic/supersonic wave (compressibility) drag
}
//############################################################################//
//horizontal lift component (vertical stabilisers and body)
void HLiftCoeff(VESSEL *v,double betta,double M,double Re,void *context,double *cl,double *cm,double *cd)
{
int i;
const int nabsc=8;
static const double BETA[nabsc]={-180*RAD,-135*RAD,-90*RAD,-45*RAD,45*RAD,90*RAD,135*RAD,180*RAD};
static const double CL[nabsc] ={ 0, +0.3, 0, -0.3, +0.3, 0, -0.3, 0};
for(i=0;i<nabsc-1 && BETA[i+1]<betta;i++);
*cl=CL[i]+(CL[i+1]-CL[i])*(betta-BETA[i])/(BETA[i+1]-BETA[i]);
*cm=0.0;
*cd=0.015+oapiGetInducedDrag(*cl,1.5,0.6)+oapiGetWaveDrag(M,0.75,1.0,1.1,0.04);
}
....
CreateAirfoil3(LIFT_VERTICAL,_V(0,0,-0.5),VLiftCoeff,0,0,1,1);
// wing and body lift+drag components
CreateAirfoil3(LIFT_HORIZONTAL,_V(0,0,-4),HLiftCoeff,0,0,1,1);
// vertical stabiliser and body lift and drag components
I didn't see any error complaining about it missing