// Module:        10520c.c
//  Author:       Phil Schubert
//  Date started: 12/03/99
//  Purpose:      Models a Continental IO-520-M Engine
//  Called by:    FGSimExec
// 
//  Copyright (C) 1999  Philip L. Schubert (philings@ozemail.com.au)
//
// This program is free software; you can redistribute it and/or
// modify it under the terms of the GNU General Public License as
// published by the Free Software Foundation; either version 2 of the
// License, or (at your option) any later version.
//
// This program is distributed in the hope that it will be useful, but
// WITHOUT ANY WARRANTY; without even the implied warranty of
// MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the GNU
// General Public License for more details.
//
// You should have received a copy of the GNU General Public License
// along with this program; if not, write to the Free Software
// Foundation, Inc., 59 Temple Place - Suite 330, Boston, MA
// 02111-1307, USA.
//
// Further information about the GNU General Public License can also
// be found on the world wide web at http://www.gnu.org.
//
// FUNCTIONAL DESCRIPTION
// ------------------------------------------------------------------------
// Models a Continental IO-520-M engine. This engine is used in Cessna
// 210, 310, Beechcraft Bonaza and Baron C55. The equations used below
// were determined by a first and second order curve fits using Excel. 
// The data is from the Cessna Aircraft Corporations Engine and Flight
// Computer for C310. Part Number D3500-13
// 
// ARGUMENTS
// ------------------------------------------------------------------------
// 
// 
// HISTORY
// ------------------------------------------------------------------------
// 12/03/99   	PLS	Created
// 07/03/99	PLS	Added Calculation of Density, and Prop_Torque
// 07/03/99	PLS	Restructered Variables to allow easier implementation
//			of Classes
// 15/03/99	PLS	Added Oil Pressure, Oil Temperature and CH Temp
// ------------------------------------------------------------------------
// INCLUDES
// ------------------------------------------------------------------------
//
//
/////////////////////////////////////////////////////////////////////
//
// Modified by Dave Luff (david.luff@nottingham.ac.uk) September 2000
//
// Altered manifold pressure range to add a minimum value at idle to simulate the throttle stop / idle bypass valve,
// and to reduce the maximum value whilst the engine is running to slightly below ambient to account for CdA losses across the throttle
//
// Altered it a bit to model an IO360 from C172 - 360 cubic inches, 180 HP max, fixed pitch prop
// Added a simple fixed pitch prop model by Nev Harbor - this is not intended as a final model but simply a hack to get it running for now
// I used Phil's ManXRPM correlation for power rather than do a new one for the C172 for now, but altered it a bit to reduce power at the low end
//
// Added EGT model based on combustion efficiency and an energy balance with the exhaust gases
//
// Added a mixture - power correlation based on a curve in the IO360 operating manual
//
// I've tried to match the prop and engine model to give roughly 600 RPM idle and 180 HP at 2700 RPM
// but it is by no means currently at a completed stage - DCL 15/9/00
//
// DCL 28/9/00 - Added estimate of engine and prop inertia and changed engine speed calculation to be calculated from Angular acceleration = Torque / Inertia.  
//		 Requires a timestep to be passed to FGNewEngine::init and currently assumes this timestep does not change.
//		 Could easily be altered to pass a variable timestep to FGNewEngine::update every step instead if required.
//
//////////////////////////////////////////////////////////////////////

#include <simgear/compiler.h>

#include <iostream>
#include <fstream>
#include <math.h>

#include "IO360.hxx"

FG_USING_STD(cout);

// ------------------------------------------------------------------------
// CODE
// ------------------------------------------------------------------------


// Calculate Engine RPM based on Propellor Lever Position
float FGNewEngine::Calc_Engine_RPM (float LeverPosition)
{
    // Calculate RPM as set by Prop Lever Position. Assumes engine
    // will run at 1000 RPM at full course
    
    float RPM;
    RPM = LeverPosition * Max_RPM / 100.0;
    // * ((FGEng_Max_RPM + FGEng_Min_RPM) / 100);
    
    if ( RPM >= Max_RPM ) {
	RPM = Max_RPM;
    }

    return RPM;
}

float FGNewEngine::Lookup_Combustion_Efficiency(float thi_actual)
{
    float thi[11];  //array of equivalence ratio values
    float neta_comb[11];  //corresponding array of combustion efficiency values
    float neta_comb_actual;
    float factor;

    //thi = (0.0,0.9,1.0,1.05,1.1,1.15,1.2,1.3,1.4,1.5,1.6);
    thi[0] = 0.0;
    thi[1] = 0.9;
    thi[2] = 1.0;
    thi[3] = 1.05;	//There must be an easier way of doing this !!!!!!!!
    thi[4] = 1.1;
    thi[5] = 1.15;
    thi[6] = 1.2;
    thi[7] = 1.3;
    thi[8] = 1.4;
    thi[9] = 1.5;
    thi[10] = 1.6;
    //neta_comb = (0.98,0.98,0.97,0.95,0.9,0.85,0.79,0.7,0.63,0.57,0.525);
    neta_comb[0] = 0.98;
    neta_comb[1] = 0.98;
    neta_comb[2] = 0.97;
    neta_comb[3] = 0.95;
    neta_comb[4] = 0.9;
    neta_comb[5] = 0.85;
    neta_comb[6] = 0.79;
    neta_comb[7] = 0.7;
    neta_comb[8] = 0.63;
    neta_comb[9] = 0.57;
    neta_comb[10] = 0.525;
    //combustion efficiency values from Heywood: ISBN 0-07-100499-8

    int i;
    int j;
    j = 11;  //This must be equal to the number of elements in the lookup table arrays

    for(i=0;i<j;i++)
    {
	if(i == (j-1))
	{
	    //this is just to avoid crashing the routine is we are bigger than the last element - for now just return the last element
	    //but at some point we will have to extrapolate further
	    neta_comb_actual = neta_comb[i];
	    return neta_comb_actual;
	}
	if(thi_actual == thi[i])
	{
	    neta_comb_actual = neta_comb[i];
	    return neta_comb_actual;
	}
	if((thi_actual > thi[i]) && (thi_actual < thi[i + 1]))
	{
	    //do linear interpolation between the two points
	    factor = (thi_actual - thi[i]) / (thi[i+1] - thi[i]);
	    neta_comb_actual = (factor * (neta_comb[i+1] - neta_comb[i])) + neta_comb[i];
	    return neta_comb_actual;
	}
    }

    //if we get here something has gone badly wrong
    cout << "ERROR: error in FGNewEngine::Lookup_Combustion_Efficiency\n";
    //exit(-1);
    return neta_comb_actual;  //keeps the compiler happy
}
/*
float FGNewEngine::Calculate_Delta_T_Exhaust(void)
{
	float dT_exhaust;
	heat_capacity_exhaust = (Cp_air * m_dot_air) + (Cp_fuel * m_dot_fuel);
	dT_exhaust = enthalpy_exhaust / heat_capacity_exhaust;

	return(dT_exhaust);
}
*/

// Calculate Manifold Pressure based on Throttle lever Position
static float Calc_Manifold_Pressure ( float LeverPosn, float MaxMan, float MinMan)
{
    float Inches;  
    // if ( x < = 0 ) {
    //   x = 0.00001;
    // }

    //Note that setting the manifold pressure as a function of lever position only is not strictly accurate
    //MAP is also a function of engine speed.
    Inches = MinMan + (LeverPosn * (MaxMan - MinMan) / 100);

    //allow for idle bypass valve or slightly open throttle stop
    if(Inches < MinMan)
	Inches = MinMan;

    return Inches;
}


// set initial default values
void FGNewEngine::init(double dt) {

    CONVERT_CUBIC_INCHES_TO_METERS_CUBED = 1.638706e-5;
    // Control and environment inputs
    IAS = 0;
    Throttle_Lever_Pos = 75;
    Propeller_Lever_Pos = 75;	
    Mixture_Lever_Pos = 100;
    Cp_air = 1005;	// J/KgK
    Cp_fuel = 1700;	// J/KgK
    calorific_value_fuel = 47.3e6;  // W/Kg  Note that this is only an approximate value
    R_air = 287.3;
    time_step = dt;

    // Engine Specific Variables used by this program that have limits.
    // Will be set in a parameter file to be read in to create
    // and instance for each engine.
    Max_Manifold_Pressure = 28.50;  //Inches Hg. An approximation - should be able to find it in the engine performance data
    Min_Manifold_Pressure = 6.5;    //Inches Hg. This is a guess corresponding to approx 0.24 bar MAP (7 in Hg) - need to find some proper data for this
    Max_RPM = 2700;
    Min_RPM = 600;		    //Recommended idle from Continental data sheet
    Max_Fuel_Flow = 130;
    Mag_Derate_Percent = 5;
//    MaxHP = 285;    //Continental IO520-M
    MaxHP = 180;    //Lycoming IO360
//  displacement = 520;  //Continental IO520-M
    displacement = 360;	 //Lycoming IO360   
    engine_inertia = 0.2;  //kgm^2 - value taken from a popular family saloon car engine - need to find an aeroengine value !!!!!
    prop_inertia = 0.03;  //kgm^2 - this value is a total guess - dcl
    displacement_SI = displacement * CONVERT_CUBIC_INCHES_TO_METERS_CUBED;

    Gear_Ratio = 1;
    started = true;
    cranking = false;

    CONVERT_HP_TO_WATTS = 745.6999;
//    ofstream outfile;
 //   outfile.open(ios::out|ios::trunc);

    // Initialise Engine Variables used by this instance
    Percentage_Power = 0;
    Manifold_Pressure = 29.00; // Inches
    RPM = 600;
    Fuel_Flow = 0;	// lbs/hour
    Torque = 0;
    CHT = 370;
    Mixture = 14;
    Oil_Pressure = 0;	// PSI
    Oil_Temp = 85;	// Deg C
    HP = 0;
    RPS = 0;
    Torque_Imbalance = 0;
    Desired_RPM = 2500;	    //Recommended cruise RPM from Continental datasheet

    // Initialise Propellor Variables used by this instance
    FGProp1_Angular_V = 0;
    FGProp1_Coef_Drag =  0.6;
    FGProp1_Torque = 0;
    FGProp1_Thrust = 0;
    FGProp1_RPS = 0;
    FGProp1_Coef_Lift = 0.1;
    Alpha1 = 13.5;
    FGProp1_Blade_Angle = 13.5;
    FGProp_Fine_Pitch_Stop = 13.5;

    // Other internal values
    Rho = 0.002378;
}


// Calculate Oil Pressure
static float Oil_Press (float Oil_Temp, float Engine_RPM)
{
    float Oil_Pressure = 0;			//PSI
    float Oil_Press_Relief_Valve = 60;	//PSI
    float Oil_Press_RPM_Max = 1800;
    float Design_Oil_Temp = 85;		//Celsius
    float Oil_Viscosity_Index = 0.25;	// PSI/Deg C
    float Temp_Deviation = 0;		// Deg C

    Oil_Pressure = (Oil_Press_Relief_Valve / Oil_Press_RPM_Max) * Engine_RPM;
	
    // Pressure relief valve opens at Oil_Press_Relief_Valve PSI setting
    if (Oil_Pressure >= Oil_Press_Relief_Valve)	
	{
	    Oil_Pressure = Oil_Press_Relief_Valve;
	}
	
    // Now adjust pressure according to Temp which affects the viscosity
	
    Oil_Pressure += (Design_Oil_Temp - Oil_Temp) * Oil_Viscosity_Index;	
	
    return Oil_Pressure;
}


// Calculate Cylinder Head Temperature
static float Calc_CHT (float Fuel_Flow, float Mixture, float IAS)
{
    float CHT = 350;
	
    return CHT;
}

/*
//Calculate Exhaust Gas Temperature
//For now we will simply adjust this as a function of mixture
//It may be necessary to consider fuel flow rates and CHT in the calculation in the future
static float Calc_EGT (float Mixture)
{
    float EGT = 1000;   //off the top of my head !!!!
    //Now adjust for mixture strength

    return EGT;
}*/


// Calculate Density Ratio
static float Density_Ratio ( float x )
{
    float y ;
    y = ((3E-10 * x * x) - (3E-05 * x) + 0.9998);
    return(y);
}


// Calculate Air Density - Rho
static float Density ( float x )
{
    float y ;
    y = ((9E-08 * x * x) - (7E-08 * x) + 0.0024);
    return(y);
}


// Calculate Speed in FPS given Knots CAS
static float IAS_to_FPS (float x)
{
    float y;
    y = x * 1.68888888;
    return y;
}


// update the engine model based on current control positions
void FGNewEngine::update() {
    // Declare local variables
    int num = 0;
    // const int num2 = 500;	// default is 100, number if iterations to run
    const int num2 = 5;	// default is 100, number if iterations to run
    float ManXRPM = 0;
    float Vo = 0;
    float V1 = 0;


    // Set up the new variables
    float Blade_Station = 30;
    float FGProp_Area = 1.405/3;
    float PI = 3.1428571;

    // Input Variables

    // 0 = Closed, 100 = Fully Open
    // float Throttle_Lever_Pos = 75;
    // 0 = Full Course 100 = Full Fine
    // float Propeller_Lever_Pos = 75;	
    // 0 = Idle Cut Off 100 = Full Rich
    // float Mixture_Lever_Pos = 100;

    // Environmental Variables

    // Temp Variation from ISA (Deg F)
    float FG_ISA_VAR = 0;
    // Pressure Altitude  1000's of Feet
    float FG_Pressure_Ht = 0;

    // Parameters that alter the operation of the engine.
    // Yes = 1. Is there Fuel Available. Calculated elsewhere
    int Fuel_Available = 1;
    // Off = 0. Reduces power by 3 % for same throttle setting
    int Alternate_Air_Pos =0;
    // 1 = On.   Reduces power by 5 % for same power lever settings
    int Magneto_Left = 1;
    // 1 = On.  Ditto, Both of the above though do not alter fuel flow
    int Magneto_Right = 1;

    // There needs to be a section in here to trap silly values, like
    // 0, otherwise they will crash the calculations

    // cout << " Number of Iterations ";
    // cin >> num2;
    // cout << endl;

    // cout << " Throttle % ";
    // cin >> Throttle_Lever_Pos;
    // cout << endl;

    // cout << " Prop % ";
    // cin >> Propeller_Lever_Pos;
    // cout << endl;

    //==================================================================
    // Engine & Environmental Inputs from elsewhere

    // Calculate Air Density (Rho) - In FG this is calculated in 
    // FG_Atomoshere.cxx

    Rho = Density(FG_Pressure_Ht); // In FG FG_Pressure_Ht is "h"
    // cout << "Rho = " << Rho << endl;

    // Calculate Manifold Pressure (Engine 1) as set by throttle opening

    Manifold_Pressure = 
	Calc_Manifold_Pressure( Throttle_Lever_Pos, Max_Manifold_Pressure, Min_Manifold_Pressure );
    // cout << "manifold pressure = " << Manifold_Pressure << endl;

    //DCL - hack for testing - fly at sea level
    T_amb = 298.0;
    p_amb = 101325;
    p_amb_sea_level = 101325;

    //DCL - next calculate m_dot_air and m_dot_fuel into engine

    //calculate actual ambient pressure and temperature from altitude
    //Then find the actual manifold pressure (the calculated one is the sea level pressure)
    True_Manifold_Pressure = Manifold_Pressure * p_amb / p_amb_sea_level;

    //    RPM = Calc_Engine_RPM(Propeller_Lever_Pos);
    // RPM = 600;
    // cout << "Initial engine RPM = " << RPM << endl;

//    Desired_RPM = RPM;

//**************	
	
	//DCL - calculate mass air flow into engine based on speed and load - separate this out into a function eventually
	//t_amb is actual temperature calculated from altitude
	//calculate density from ideal gas equation
	rho_air = p_amb / ( R_air * T_amb );
	rho_air_manifold = rho_air * Manifold_Pressure / 29.6;
	//calculate ideal engine volume inducted per second
	swept_volume = (displacement_SI * (RPM / 60)) / 2;  //This equation is only valid for a four stroke engine
	//calculate volumetric efficiency - for now we will just use 0.8, but actually it is a function of engine speed and the exhaust to manifold pressure ratio
	volumetric_efficiency = 0.8;
	//Now use volumetric efficiency to calculate actual air volume inducted per second
	v_dot_air = swept_volume * volumetric_efficiency;
	//Now calculate mass flow rate of air into engine
	m_dot_air = v_dot_air * rho_air_manifold;

	// cout << "rho air manifold " << rho_air_manifold << '\n';
	// cout << "Swept volume " << swept_volume << '\n';

//**************

	//DCL - now calculate fuel flow into engine based on air flow and mixture lever position
	//assume lever runs from no flow at fully out to thi = 1.6 at fully in at sea level
	//also assume that the injector linkage is ideal - hence the set mixture is maintained at a given altitude throughout the speed and load range
	thi_sea_level = 1.6 * ( Mixture_Lever_Pos / 100.0 );
	equivalence_ratio = thi_sea_level * p_amb_sea_level / p_amb; //ie as we go higher the mixture gets richer for a given lever position
	m_dot_fuel = m_dot_air / 14.7 * equivalence_ratio;

	// cout << "fuel " << m_dot_fuel;
	// cout << " air " << m_dot_air << '\n';

//**************

	// cout << "Thi = " << equivalence_ratio << '\n'; 

	combustion_efficiency = Lookup_Combustion_Efficiency(equivalence_ratio);  //The combustion efficiency basically tells us what proportion of the fuels calorific value is released

	// cout << "Combustion efficiency = " << combustion_efficiency << '\n';

	//now calculate energy release to exhaust
	//We will assume a three way split of fuel energy between useful work, the coolant system and the exhaust system
	//This is a reasonable first suck of the thumb estimate for a water cooled automotive engine - whether it holds for an air cooled aero engine is probably open to question
	//Regardless - it won't affect the variation of EGT with mixture, and we con always put a multiplier on EGT to get a reasonable peak value.
	enthalpy_exhaust = m_dot_fuel * calorific_value_fuel * combustion_efficiency * 0.33;
	heat_capacity_exhaust = (Cp_air * m_dot_air) + (Cp_fuel * m_dot_fuel);
	delta_T_exhaust = enthalpy_exhaust / heat_capacity_exhaust;	
//	delta_T_exhaust = Calculate_Delta_T_Exhaust();

	// cout << "T_amb " << T_amb;
	// cout << " dT exhaust = " << delta_T_exhaust;

	EGT = T_amb + delta_T_exhaust;

	// cout << " EGT = " << EGT << '\n';

 
    // Calculate Manifold Pressure (Engine 2) as set by throttle opening

    // FGEng2_Manifold_Pressure = Manifold_Pressure(FGEng2_Throttle_Lever_Pos, FGEng2_Manifold_Pressure);
    // Show_Manifold_Pressure(FGEng2_Manifold_Pressure);



    //==================================================================
    // Engine Power & Torque Calculations

    // Loop until stable - required for testing only
//    for (num = 0; num < num2; num++) {
	// cout << Manifold_Pressure << " Inches" << "\t";
	// cout << RPM << "  RPM" << "\t";

	// For a given Manifold Pressure and RPM calculate the % Power
	// Multiply Manifold Pressure by RPM
	ManXRPM = Manifold_Pressure * RPM;
	//	cout << ManXRPM;
	// cout << endl;

//  Phil's %power correlation
/*	//  Calculate % Power
	Percentage_Power = (+ 7E-09 * ManXRPM * ManXRPM) 
	    + ( + 7E-04 * ManXRPM) - 0.1218;
	// cout << Percentage_Power <<  "%" << "\t";   */  

// DCL %power correlation - basically Phil's correlation modified to give slighty less power at the low end
// might need some adjustment as the prop model is adjusted
// My aim is to match the prop model and engine model at the low end to give the manufacturer's recommended idle speed with the throttle closed - 600rpm for the Continental IO520
	//  Calculate % Power
	Percentage_Power = (+ 6E-09 * ManXRPM * ManXRPM) 
	    + ( + 8E-04 * ManXRPM) - 1.8524;
	// cout << Percentage_Power <<  "%" << "\t";

	// Adjust for Temperature - Temperature above Standard decrease
	// power % by 7/120 per degree F increase, and incease power for
	// temps below at the same ratio
	Percentage_Power = Percentage_Power - (FG_ISA_VAR * 7 /120);
	// cout << Percentage_Power <<  "%" << "\t";
    
	// Adjust for Altitude. In this version a linear variation is
	// used. Decrease 1% for each 1000' increase in Altitde
	Percentage_Power = Percentage_Power + (FG_Pressure_Ht * 12/10000);	
	// cout << Percentage_Power <<  "%" << "\t";

	//DCL - now adjust power to compensate for mixture
	//uses a curve fit to the data in the IO360 / O360 operating manual
	//due to the shape of the curve I had to use a 6th order fit - I am sure it must be possible to reduce this in future,
	//possibly by using separate fits for rich and lean of best power mixture
	//first adjust actual mixture to abstract mixture - this is a temporary hack in order to account for the fact that the data I have
	//dosn't specify actual mixtures and I want to be able to change what I think they are without redoing the curve fit each time.
	//y=10x-12 for now
	abstract_mixture = 10.0 * equivalence_ratio - 12.0;
	float m = abstract_mixture;  //to simplify writing the next equation
	Percentage_of_best_power_mixture_power = ((-0.0012*m*m*m*m*m*m) + (0.021*m*m*m*m*m) + (-0.1425*m*m*m*m) + (0.4395*m*m*m) + (-0.8909*m*m) + (-0.5155*m) + 100.03);
	Percentage_Power = Percentage_Power * Percentage_of_best_power_mixture_power / 100.0;
	

	// Now Calculate Fuel Flow based on % Power Best Power Mixture
	Fuel_Flow = Percentage_Power * Max_Fuel_Flow / 100.0;
	// cout << Fuel_Flow << " lbs/hr"<< endl;
	
	// Now Derate engine for the effects of Bad/Switched off magnetos
	if (Magneto_Left == 0 && Magneto_Right == 0) {
	    // cout << "Both OFF\n";
	    Percentage_Power = 0;
	} else if (Magneto_Left && Magneto_Right) {
	    // cout << "Both On    ";
	} else if (Magneto_Left == 0 || Magneto_Right== 0) {
	    // cout << "1 Magneto Failed   ";

	    Percentage_Power = Percentage_Power * 
		((100.0 - Mag_Derate_Percent)/100.0);
	    //  cout << FGEng1_Percentage_Power <<  "%" << "\t";
	}	

	// Calculate Engine Horsepower

	HP = Percentage_Power * MaxHP / 100.0;

	Power_SI = HP * CONVERT_HP_TO_WATTS;

	// Calculate Engine Torque

	Torque = HP * 5252 / RPM;
	// cout << Torque << "Ft/lbs" << "\t";

	Torque_SI = (Power_SI * 60.0) / (2.0 * PI * RPM);  //Torque = power / angular velocity
	// cout << Torque << " Nm\n";

	// Calculate Cylinder Head Temperature
	CHT = Calc_CHT( Fuel_Flow, Mixture, IAS);
	// cout << "Cylinder Head Temp (F) = " << CHT << endl;

//	EGT = Calc_EGT( Mixture );

	// Calculate Oil Pressure
	Oil_Pressure = Oil_Press( Oil_Temp, RPM );
	// cout << "Oil Pressure (PSI) = " << Oil_Pressure << endl;
	
	//==============================================================

	// Now do the Propellor Calculations

#ifdef PHILS_PROP_MODEL

	// Revs per second
	FGProp1_RPS = RPM * Gear_Ratio / 60.0;
	// cout << FGProp1_RPS << " RPS" <<  endl;

	//Radial Flow Vector (V2) Ft/sec at Ref Blade Station (usually 30")
	FGProp1_Angular_V = FGProp1_RPS * 2 * PI * (Blade_Station / 12);
	//  cout << FGProp1_Angular_V << "Angular Velocity "  << endl;

	// Axial Flow Vector (Vo) Ft/sec
	// Some further work required here to allow for inflow at low speeds
	// Vo = (IAS + 20) * 1.688888;
	Vo = IAS_to_FPS(IAS + 20);
	// cout << "Feet/sec = " << Vo << endl;

	// cout << Vo << "Axial Velocity" << endl;

	// Relative Velocity (V1)
	V1 = sqrt((FGProp1_Angular_V * FGProp1_Angular_V) +
		  (Vo * Vo));
	// cout << V1 << "Relative Velocity " << endl;

	// cout << FGProp1_Blade_Angle << " Prop Blade Angle" << endl;

	// Blade Angle of Attack (Alpha1)

/*	cout << "  Alpha1 = " << Alpha1
	     << "  Blade angle = " << FGProp1_Blade_Angle
	     << "  Vo = " << Vo
	     << "  FGProp1_Angular_V = " << FGProp1_Angular_V << endl;*/
	Alpha1 = FGProp1_Blade_Angle -(atan(Vo / FGProp1_Angular_V) * (180/PI));
	// cout << Alpha1 << " Alpha1" << endl;

	// Calculate Coefficient of Drag at Alpha1
	FGProp1_Coef_Drag = (0.0005 * (Alpha1 * Alpha1)) + (0.0003 * Alpha1)
	    + 0.0094;
	//	cout << FGProp1_Coef_Drag << " Coef Drag" << endl;

	// Calculate Coefficient of Lift at Alpha1
	FGProp1_Coef_Lift = -(0.0026 * (Alpha1 * Alpha1)) + (0.1027 * Alpha1)
	    + 0.2295;
	// cout << FGProp1_Coef_Lift << " Coef Lift " << endl;

	// Covert Alplha1 to Radians
	// Alpha1 = Alpha1 * PI / 180;

	//  Calculate Prop Torque
	FGProp1_Torque = (0.5 * Rho * (V1 * V1) * FGProp_Area
			  * ((FGProp1_Coef_Lift * sin(Alpha1 * PI / 180))
			     + (FGProp1_Coef_Drag * cos(Alpha1 * PI / 180))))
	    * (Blade_Station/12);
	// cout <<  FGProp1_Torque << " Prop Torque" << endl;

	//  Calculate Prop Thrust
	// cout << "  V1 = " << V1 << "  Alpha1 = " << Alpha1 << endl;
	FGProp1_Thrust = 0.5 * Rho * (V1 * V1) * FGProp_Area
	    * ((FGProp1_Coef_Lift * cos(Alpha1 * PI / 180))
	       - (FGProp1_Coef_Drag * sin(Alpha1 * PI / 180)));
	// cout << FGProp1_Thrust << " Prop Thrust " <<  endl;

	// End of Propeller Calculations   
	//==============================================================

#endif  //PHILS_PROP_MODEL

#ifdef NEVS_PROP_MODEL

	// Nev's prop model

	num_elements = 6.0;
	number_of_blades = 2.0;
	blade_length = 0.95;
	allowance_for_spinner = blade_length / 12.0;
	prop_fudge_factor = 1.453401525;
	forward_velocity = IAS;

	theta[0] = 25.0;
	theta[1] = 20.0;
	theta[2] = 15.0;
	theta[3] = 10.0;
	theta[4] = 5.0;
	theta[5] = 0.0;

	angular_velocity_SI = 2.0 * PI * RPM / 60.0;

	allowance_for_spinner = blade_length / 12.0;
	//Calculate thrust and torque by summing the contributions from each of the blade elements
	//Assumes equal length elements with numbered 1 inboard -> num_elements outboard
	prop_torque = 0.0;
	prop_thrust = 0.0;
	int i;
//	outfile << "Rho = " << Rho << '\n\n';
//	outfile << "Drag = ";
	for(i=1;i<=num_elements;i++)
	{
	    element = float(i);
	    distance = (blade_length * (element / num_elements)) + allowance_for_spinner; 
	    element_drag = 0.5 * rho_air * ((distance * angular_velocity_SI)*(distance * angular_velocity_SI)) * (0.000833 * ((theta[int(element-1)] - (atan(forward_velocity/(distance * angular_velocity_SI))))*(theta[int(element-1)] - (atan(forward_velocity/(distance * angular_velocity_SI))))))
			    * (0.1 * (blade_length / element)) * number_of_blades;

	    element_lift = 0.5 * rho_air * ((distance * angular_velocity_SI)*(distance * angular_velocity_SI)) * (0.036 * (theta[int(element-1)] - (atan(forward_velocity/(distance * angular_velocity_SI))))+0.4)
			    * (0.1 * (blade_length / element)) * number_of_blades;
	    element_torque = element_drag * distance;
	    prop_torque += element_torque;
	    prop_thrust += element_lift;
//	    outfile << "Drag = " << element_drag << " n = " << element << '\n';
	}

//	outfile << '\n';

//	outfile << "Angular velocity = " << angular_velocity_SI << " rad/s\n";

	// cout << "Thrust = " << prop_thrust << '\n';
	prop_thrust *= prop_fudge_factor;
	prop_torque *= prop_fudge_factor;
	prop_power_consumed_SI = prop_torque * angular_velocity_SI;
	prop_power_consumed_HP = prop_power_consumed_SI / 745.699;


#endif //NEVS_PROP_MODEL


//#if 0
#ifdef PHILS_PROP_MODEL  //Do Torque calculations in Ft/lbs - yuk :-(((
	Torque_Imbalance = FGProp1_Torque - Torque; 

	if (Torque_Imbalance > 5) {
	    RPM -= 14.5;
	    // FGProp1_RPM -= 25;
//	    FGProp1_Blade_Angle -= 0.75;
	}

	if (Torque_Imbalance < -5) {
	    RPM += 14.5;
	    // FGProp1_RPM += 25;
//	    FGProp1_Blade_Angle += 0.75;
	}
#endif


#ifdef NEVS_PROP_MODEL	    //use proper units - Nm
	Torque_Imbalance = Torque_SI - prop_torque;  //This gives a +ve value when the engine torque exeeds the prop torque

	angular_acceleration = Torque_Imbalance / (engine_inertia + prop_inertia);
	angular_velocity_SI += (angular_acceleration * time_step);
	RPM = (angular_velocity_SI * 60) / (2.0 * PI);
#endif



/*
	if( RPM > (Desired_RPM + 2)) {
	    FGProp1_Blade_Angle += 0.75;  //This value could be altered depending on how far from the desired RPM we are
	}

	if( RPM < (Desired_RPM - 2)) {
	    FGProp1_Blade_Angle -= 0.75;
	}

	if (FGProp1_Blade_Angle < FGProp_Fine_Pitch_Stop) {
	    FGProp1_Blade_Angle = FGProp_Fine_Pitch_Stop;
	}

	if (RPM >= 2700) {
	    RPM = 2700;
	}
*/
	//end constant speed prop
//#endif

	//DCL - stall the engine if RPM drops below 550 - this is possible if mixture lever is pulled right out
	if(RPM < 550)
	    RPM = 0;

//	outfile << "RPM = " << RPM << " Blade angle = " << FGProp1_Blade_Angle << " Engine torque = " << Torque << " Prop torque = " << FGProp1_Torque << '\n';
//	outfile << "RPM = " << RPM << " Engine torque = " << Torque_SI << " Prop torque = " << prop_torque << '\n';    

	// cout << FGEng1_RPM << " Blade_Angle  " << FGProp1_Blade_Angle << endl << endl;



    // cout << "Final engine RPM = " << RPM << '\n';
}




// Functions

// Calculate Oil Temperature

static float Oil_Temp (float Fuel_Flow, float Mixture, float IAS)
{
    float Oil_Temp = 85;
	
    return (Oil_Temp);
}