/// <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); }