/// <summary>
/// Calculate the drag for the given speed and altitude
/// </summary>
/// <param name="airspeed">The current airspeed</param>
/// <param name="altitude">The current altitude</param>
/// <returns></returns>
public double Drag(double airspeed, double altitude)
{
double ktsToMps = 0.514444444;
airspeed = (airspeed * ktsToMps);
var isa = new ISA(altitude);
double dragPolar = DragPolar(isa.Rho, airspeed);
return(dragPolar * 0.5 * isa.Rho * airspeed * airspeed * ReferenceArea);
}
/// <summary>
/// Calculate the climb thrust
/// </summary>
/// <param name="TAS">The current True AirSpeed</param>
/// <param name="altitude">The current altitude</param>
/// <returns></returns>
public double ClimbThrust(double TAS, double altitude)
{
double ktsToMps = 0.514444444;
double lbfToN = 4.4482216;
var isa = new ISA(altitude);
double machNumber = (TAS * ktsToMps) / isa.VSound;
return(lbfToN * NumberOfEngines * isa.Delta * (
(52150 + 0.72668 * altitude - 0.000015837 * altitude * altitude) +
(-53118 + 1.2828 * altitude - 0.0000084802 * altitude * altitude) * machNumber +
(26330 - 0.89757 * altitude - 0.00001585 * altitude * altitude) * machNumber * machNumber
));
}
/// <summary>
/// Calculate the takeoff thrust
/// </summary>
/// <param name="TAS">The current True AirSpeed</param>
/// <param name="altitude">The current altitude</param>
/// <returns></returns>
public double TakeOffThrust(double TAS, double altitude)
{
double ktsToMps = 0.514444444;
double lbfToN = 4.4482216;
var isa = new ISA(altitude);
double machNumber = (TAS * ktsToMps) / isa.VSound;
//Console.WriteLine(isa.P);
//Console.WriteLine(machNumber);
return(lbfToN * NumberOfEngines * isa.Delta * (
(56283 + 1.3231 * altitude - 0.000048825 * altitude * altitude) +
(-55343 - 0.41746 * altitude + 0.000013332 * altitude * altitude) * machNumber +
(37825 + 1.1609 * altitude - 0.000031028 * altitude * altitude) * machNumber * machNumber
));
}
/// <summary>
/// Calculate the amound of fuel is consumed in kilograms per second
/// </summary>
/// <param name="totalThrust">The total amound of thrust delivered by all engines</param>
/// <param name="TAS">The current True AirSpeed</param>
/// <param name="altitude">The current altitude</param>
/// <returns></returns>
public double FuelFLow(double totalThrust, double TAS, double altitude)
{
double ktsToMps = 0.514444444;
double lbsToKg = 0.45359237;
var isa = new ISA(altitude);
double machNumber = (TAS * ktsToMps) / isa.VSound;
double thrust = totalThrust / NumberOfEngines;
double thrustNormalized = thrust / isa.Delta;
double temperatureRatio = isa.Theta;
return(NumberOfEngines * isa.Delta * Math.Pow(temperatureRatio, 0.62) * (
(826.15 + 2140.5 * machNumber - 382.94 * machNumber * machNumber) +
(0.2332 + 0.14859 * machNumber - 0.095481 * machNumber * machNumber) * thrustNormalized +
(0.000001461 + 0.00000901 * machNumber - 0.000010795 * machNumber * machNumber) * thrustNormalized * thrustNormalized
) / 3600.0 * lbsToKg);
}
