/// <summary>
/// Calculates the drag force generated by the fuselage and vertical tail.
/// </summary>
/// <returns></returns>
private double GetSideDragForce(Vector3 wind)
{
return(ApiAircraftParameters.GetSideDragCoefficient(Beta) *
((ApiModel.Vx + wind.X) * (ApiModel.Vx + wind.X) + (ApiModel.Vy + wind.Y) * (ApiModel.Vy + wind.Y)) * rhoVerticalSurface);
}
/// <summary>
/// Calculates the drag force.
/// </summary>
/// <returns></returns>
private double GetDragForce(Vector3 wind)
{
// F = (1/2)*Dc*V^2*S
return(ApiAircraftParameters.GetDragCoefficient(ApiModel.Alpha, 0.0) *
((ApiModel.Vx + wind.X) * (ApiModel.Vx + wind.X) + (ApiModel.Vz + wind.Z) * (ApiModel.Vz + wind.Z)) * rhoSurface);
}
