2 // Author: Phil Schubert
3 // Date started: 12/03/99
4 // Purpose: Models a Continental IO-520-M Engine
5 // Called by: FGSimExec
7 // Copyright (C) 1999 Philip L. Schubert (philings@ozemail.com.au)
9 // This program is free software; you can redistribute it and/or
10 // modify it under the terms of the GNU General Public License as
11 // published by the Free Software Foundation; either version 2 of the
12 // License, or (at your option) any later version.
14 // This program is distributed in the hope that it will be useful, but
15 // WITHOUT ANY WARRANTY; without even the implied warranty of
16 // MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU
17 // General Public License for more details.
19 // You should have received a copy of the GNU General Public License
20 // along with this program; if not, write to the Free Software
21 // Foundation, Inc., 59 Temple Place - Suite 330, Boston, MA
24 // Further information about the GNU General Public License can also
25 // be found on the world wide web at http://www.gnu.org.
27 // FUNCTIONAL DESCRIPTION
28 // ------------------------------------------------------------------------
29 // Models a Continental IO-520-M engine. This engine is used in Cessna
30 // 210, 310, Beechcraft Bonaza and Baron C55. The equations used below
31 // were determined by a first and second order curve fits using Excel.
32 // The data is from the Cessna Aircraft Corporations Engine and Flight
33 // Computer for C310. Part Number D3500-13
36 // ------------------------------------------------------------------------
40 // ------------------------------------------------------------------------
41 // 12/03/99 PLS Created
42 // 07/03/99 PLS Added Calculation of Density, and Prop_Torque
43 // 07/03/99 PLS Restructered Variables to allow easier implementation
45 // 15/03/99 PLS Added Oil Pressure, Oil Temperature and CH Temp
46 // ------------------------------------------------------------------------
48 // ------------------------------------------------------------------------
51 /////////////////////////////////////////////////////////////////////
53 // Modified by Dave Luff (david.luff@nottingham.ac.uk) September 2000
55 // Altered manifold pressure range to add a minimum value at idle to simulate the throttle stop / idle bypass valve,
56 // and to reduce the maximum value whilst the engine is running to slightly below ambient to account for CdA losses across the throttle
58 // Altered it a bit to model an IO360 from C172 - 360 cubic inches, 180 HP max, fixed pitch prop
59 // 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
60 // 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
62 // Added EGT model based on combustion efficiency and an energy balance with the exhaust gases
64 // Added a mixture - power correlation based on a curve in the IO360 operating manual
66 // I've tried to match the prop and engine model to give roughly 600 RPM idle and 180 HP at 2700 RPM
67 // but it is by no means currently at a completed stage - DCL 15/9/00
69 //////////////////////////////////////////////////////////////////////
78 // ------------------------------------------------------------------------
80 // ------------------------------------------------------------------------
83 // Calculate Engine RPM based on Propellor Lever Position
84 float FGEngine::Calc_Engine_RPM (float LeverPosition)
86 // Calculate RPM as set by Prop Lever Position. Assumes engine
87 // will run at 1000 RPM at full course
90 RPM = LeverPosition * Max_RPM / 100.0;
91 // * ((FGEng_Max_RPM + FGEng_Min_RPM) / 100);
93 if ( RPM >= Max_RPM ) {
100 float FGEngine::Lookup_Combustion_Efficiency(float thi_actual)
102 float thi[11]; //array of equivalence ratio values
103 float neta_comb[11]; //corresponding array of combustion efficiency values
104 float neta_comb_actual;
107 //thi = (0.0,0.9,1.0,1.05,1.1,1.15,1.2,1.3,1.4,1.5,1.6);
111 thi[3] = 1.05; //There must be an easier way of doing this !!!!!!!!
119 //neta_comb = (0.98,0.98,0.97,0.95,0.9,0.85,0.79,0.7,0.63,0.57,0.525);
130 neta_comb[10] = 0.525;
131 //combustion efficiency values from Heywood [1]
135 j = 11; //This must be equal to the number of elements in the lookup table arrays
141 //this is just to avoid crashing the routine is we are bigger than the last element - for now just return the last element
142 //but at some point we will have to extrapolate further
143 neta_comb_actual = neta_comb[i];
144 return neta_comb_actual;
146 if(thi_actual == thi[i])
148 neta_comb_actual = neta_comb[i];
149 return neta_comb_actual;
151 if((thi_actual > thi[i]) && (thi_actual < thi[i + 1]))
153 //do linear interpolation between the two points
154 factor = (thi_actual - thi[i]) / (thi[i+1] - thi[i]);
155 neta_comb_actual = (factor * (neta_comb[i+1] - neta_comb[i])) + neta_comb[i];
156 return neta_comb_actual;
160 //if we get here something has gone badly wrong
161 cout << "ERROR: error in FGEngine::Lookup_Combustion_Efficiency\n";
163 return neta_comb_actual; //keeps the compiler happy
166 float FGEngine::Calculate_Delta_T_Exhaust(void)
169 heat_capacity_exhaust = (Cp_air * m_dot_air) + (Cp_fuel * m_dot_fuel);
170 dT_exhaust = enthalpy_exhaust / heat_capacity_exhaust;
176 // Calculate Manifold Pressure based on Throttle lever Position
177 static float Calc_Manifold_Pressure ( float LeverPosn, float MaxMan, float MinMan)
184 //Note that setting the manifold pressure as a function of lever position only is not strictly accurate
185 //MAP is also a function of engine speed.
186 Inches = MinMan + (LeverPosn * (MaxMan - MinMan) / 100);
188 //allow for idle bypass valve or slightly open throttle stop
196 // set initial default values
197 void FGEngine::init() {
199 CONVERT_CUBIC_INCHES_TO_METERS_CUBED = 1.638706e-5;
200 // Control and environment inputs
202 Throttle_Lever_Pos = 75;
203 Propeller_Lever_Pos = 75;
204 Mixture_Lever_Pos = 100;
205 Cp_air = 1005; // J/KgK
206 Cp_fuel = 1700; // J/KgK
207 calorific_value_fuel = 47.3e6; // W/Kg Note that this is only an approximate value
210 // Engine Specific Variables used by this program that have limits.
211 // Will be set in a parameter file to be read in to create
212 // and instance for each engine.
213 Max_Manifold_Pressure = 28.50; //Inches Hg. An approximation - should be able to find it in the engine performance data
214 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
216 Min_RPM = 600; //Recommended idle from Continental data sheet
218 Mag_Derate_Percent = 5;
219 // MaxHP = 285; //Continental IO520-M
220 MaxHP = 180; //Lycoming IO360
221 // displacement = 520; //Continental IO520-M
222 displacement = 360; //Lycoming IO360
223 displacement_SI = displacement * CONVERT_CUBIC_INCHES_TO_METERS_CUBED;
229 CONVERT_HP_TO_WATTS = 745.6999;
231 // outfile.open(ios::out|ios::trunc);
233 // Initialise Engine Variables used by this instance
234 Percentage_Power = 0;
235 Manifold_Pressure = 29.00; // Inches
237 Fuel_Flow = 0; // lbs/hour
241 Oil_Pressure = 0; // PSI
242 Oil_Temp = 85; // Deg C
245 Torque_Imbalance = 0;
246 Desired_RPM = 2500; //Recommended cruise RPM from Continental datasheet
248 // Initialise Propellor Variables used by this instance
249 FGProp1_Angular_V = 0;
250 FGProp1_Coef_Drag = 0.6;
254 FGProp1_Coef_Lift = 0.1;
256 FGProp1_Blade_Angle = 13.5;
257 FGProp_Fine_Pitch_Stop = 13.5;
259 // Other internal values
264 // Calculate Oil Pressure
265 static float Oil_Press (float Oil_Temp, float Engine_RPM)
267 float Oil_Pressure = 0; //PSI
268 float Oil_Press_Relief_Valve = 60; //PSI
269 float Oil_Press_RPM_Max = 1800;
270 float Design_Oil_Temp = 85; //Celsius
271 float Oil_Viscosity_Index = 0.25; // PSI/Deg C
272 float Temp_Deviation = 0; // Deg C
274 Oil_Pressure = (Oil_Press_Relief_Valve / Oil_Press_RPM_Max) * Engine_RPM;
276 // Pressure relief valve opens at Oil_Press_Relief_Valve PSI setting
277 if (Oil_Pressure >= Oil_Press_Relief_Valve)
279 Oil_Pressure = Oil_Press_Relief_Valve;
282 // Now adjust pressure according to Temp which affects the viscosity
284 Oil_Pressure += (Design_Oil_Temp - Oil_Temp) * Oil_Viscosity_Index;
290 // Calculate Cylinder Head Temperature
291 static float Calc_CHT (float Fuel_Flow, float Mixture, float IAS)
299 //Calculate Exhaust Gas Temperature
300 //For now we will simply adjust this as a function of mixture
301 //It may be necessary to consider fuel flow rates and CHT in the calculation in the future
302 static float Calc_EGT (float Mixture)
304 float EGT = 1000; //off the top of my head !!!!
305 //Now adjust for mixture strength
311 // Calculate Density Ratio
312 static float Density_Ratio ( float x )
315 y = ((3E-10 * x * x) - (3E-05 * x) + 0.9998);
320 // Calculate Air Density - Rho
321 static float Density ( float x )
324 y = ((9E-08 * x * x) - (7E-08 * x) + 0.0024);
329 // Calculate Speed in FPS given Knots CAS
330 static float IAS_to_FPS (float x)
338 // update the engine model based on current control positions
339 void FGEngine::update() {
340 // Declare local variables
342 // const int num2 = 500; // default is 100, number if iterations to run
343 const int num2 = 5; // default is 100, number if iterations to run
349 // Set up the new variables
350 float Blade_Station = 30;
351 float FGProp_Area = 1.405/3;
352 float PI = 3.1428571;
356 // 0 = Closed, 100 = Fully Open
357 // float Throttle_Lever_Pos = 75;
358 // 0 = Full Course 100 = Full Fine
359 // float Propeller_Lever_Pos = 75;
360 // 0 = Idle Cut Off 100 = Full Rich
361 // float Mixture_Lever_Pos = 100;
363 // Environmental Variables
365 // Temp Variation from ISA (Deg F)
366 float FG_ISA_VAR = 0;
367 // Pressure Altitude 1000's of Feet
368 float FG_Pressure_Ht = 0;
370 // Parameters that alter the operation of the engine.
371 // Yes = 1. Is there Fuel Available. Calculated elsewhere
372 int Fuel_Available = 1;
373 // Off = 0. Reduces power by 3 % for same throttle setting
374 int Alternate_Air_Pos =0;
375 // 1 = On. Reduces power by 5 % for same power lever settings
376 int Magneto_Left = 1;
377 // 1 = On. Ditto, Both of the above though do not alter fuel flow
378 int Magneto_Right = 1;
380 // There needs to be a section in here to trap silly values, like
381 // 0, otherwise they will crash the calculations
383 // cout << " Number of Iterations ";
387 // cout << " Throttle % ";
388 // cin >> Throttle_Lever_Pos;
391 // cout << " Prop % ";
392 // cin >> Propeller_Lever_Pos;
395 //==================================================================
396 // Engine & Environmental Inputs from elsewhere
398 // Calculate Air Density (Rho) - In FG this is calculated in
401 Rho = Density(FG_Pressure_Ht); // In FG FG_Pressure_Ht is "h"
402 // cout << "Rho = " << Rho << endl;
404 // Calculate Manifold Pressure (Engine 1) as set by throttle opening
407 Calc_Manifold_Pressure( Throttle_Lever_Pos, Max_Manifold_Pressure, Min_Manifold_Pressure );
408 // cout << "manifold pressure = " << Manifold_Pressure << endl;
410 //DCL - hack for testing - fly at sea level
413 p_amb_sea_level = 101325;
415 //DCL - next calculate m_dot_air and m_dot_fuel into engine
417 //calculate actual ambient pressure and temperature from altitude
418 //Then find the actual manifold pressure (the calculated one is the sea level pressure)
419 True_Manifold_Pressure = Manifold_Pressure * p_amb / p_amb_sea_level;
421 // RPM = Calc_Engine_RPM(Propeller_Lever_Pos);
423 // cout << "Initial engine RPM = " << RPM << endl;
425 // Desired_RPM = RPM;
429 //DCL - calculate mass air flow into engine based on speed and load - separate this out into a function eventually
430 //t_amb is actual temperature calculated from altitude
431 //calculate density from ideal gas equation
432 rho_air = p_amb / ( R_air * T_amb );
433 rho_air_manifold = rho_air * Manifold_Pressure / 29.6;
434 //calculate ideal engine volume inducted per second
435 swept_volume = (displacement_SI * (RPM / 60)) / 2; //This equation is only valid for a four stroke engine
436 //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
437 volumetric_efficiency = 0.8;
438 //Now use volumetric efficiency to calculate actual air volume inducted per second
439 v_dot_air = swept_volume * volumetric_efficiency;
440 //Now calculate mass flow rate of air into engine
441 m_dot_air = v_dot_air * rho_air_manifold;
443 // cout << "rho air manifold " << rho_air_manifold << '\n';
444 // cout << "Swept volume " << swept_volume << '\n';
448 //DCL - now calculate fuel flow into engine based on air flow and mixture lever position
449 //assume lever runs from no flow at fully out to thi = 1.6 at fully in at sea level
450 //also assume that the injector linkage is ideal - hence the set mixture is maintained at a given altitude throughout the speed and load range
451 thi_sea_level = 1.6 * ( Mixture_Lever_Pos / 100.0 );
452 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
453 m_dot_fuel = m_dot_air / 14.7 * equivalence_ratio;
455 // cout << "fuel " << m_dot_fuel;
456 // cout << " air " << m_dot_air << '\n';
460 // cout << "Thi = " << equivalence_ratio << '\n';
462 combustion_efficiency = Lookup_Combustion_Efficiency(equivalence_ratio); //The combustion efficiency basically tells us what proportion of the fuels calorific value is released
464 // cout << "Combustion efficiency = " << combustion_efficiency << '\n';
466 //now calculate energy release to exhaust
467 //We will assume a three way split of fuel energy between useful work, the coolant system and the exhaust system
468 //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
469 //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.
470 enthalpy_exhaust = m_dot_fuel * calorific_value_fuel * combustion_efficiency * 0.33;
471 heat_capacity_exhaust = (Cp_air * m_dot_air) + (Cp_fuel * m_dot_fuel);
472 delta_T_exhaust = enthalpy_exhaust / heat_capacity_exhaust;
473 // delta_T_exhaust = Calculate_Delta_T_Exhaust();
475 // cout << "T_amb " << T_amb;
476 // cout << " dT exhaust = " << delta_T_exhaust;
478 EGT = T_amb + delta_T_exhaust;
480 // cout << " EGT = " << EGT << '\n';
483 // Calculate Manifold Pressure (Engine 2) as set by throttle opening
485 // FGEng2_Manifold_Pressure = Manifold_Pressure(FGEng2_Throttle_Lever_Pos, FGEng2_Manifold_Pressure);
486 // Show_Manifold_Pressure(FGEng2_Manifold_Pressure);
490 //==================================================================
491 // Engine Power & Torque Calculations
493 // Loop until stable - required for testing only
494 for (num = 0; num < num2; num++) {
495 // cout << Manifold_Pressure << " Inches" << "\t";
496 // cout << RPM << " RPM" << "\t";
498 // For a given Manifold Pressure and RPM calculate the % Power
499 // Multiply Manifold Pressure by RPM
500 ManXRPM = Manifold_Pressure * RPM;
504 // Phil's %power correlation
505 /* // Calculate % Power
506 Percentage_Power = (+ 7E-09 * ManXRPM * ManXRPM)
507 + ( + 7E-04 * ManXRPM) - 0.1218;
508 // cout << Percentage_Power << "%" << "\t"; */
510 // DCL %power correlation - basically Phil's correlation modified to give slighty less power at the low end
511 // might need some adjustment as the prop model is adjusted
512 // 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
514 Percentage_Power = (+ 6E-09 * ManXRPM * ManXRPM)
515 + ( + 8E-04 * ManXRPM) - 1.8524;
516 // cout << Percentage_Power << "%" << "\t";
518 // Adjust for Temperature - Temperature above Standard decrease
519 // power % by 7/120 per degree F increase, and incease power for
520 // temps below at the same ratio
521 Percentage_Power = Percentage_Power - (FG_ISA_VAR * 7 /120);
522 // cout << Percentage_Power << "%" << "\t";
524 // Adjust for Altitude. In this version a linear variation is
525 // used. Decrease 1% for each 1000' increase in Altitde
526 Percentage_Power = Percentage_Power + (FG_Pressure_Ht * 12/10000);
527 // cout << Percentage_Power << "%" << "\t";
529 //DCL - now adjust power to compensate for mixture
530 //uses a curve fit to the data in the IO360 / O360 operating manual
531 //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,
532 //possibly by using separate fits for rich and lean of best power mixture
533 //first adjust actual mixture to abstract mixture - this is a temporary hack
535 abstract_mixture = 10.0 * equivalence_ratio - 12.0;
536 float m = abstract_mixture; //to simplify writing the next equation
537 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);
538 Percentage_Power = Percentage_Power * Percentage_of_best_power_mixture_power / 100.0;
541 // Now Calculate Fuel Flow based on % Power Best Power Mixture
542 Fuel_Flow = Percentage_Power * Max_Fuel_Flow / 100.0;
543 // cout << Fuel_Flow << " lbs/hr"<< endl;
545 // Now Derate engine for the effects of Bad/Switched off magnetos
546 if (Magneto_Left == 0 && Magneto_Right == 0) {
547 // cout << "Both OFF\n";
548 Percentage_Power = 0;
549 } else if (Magneto_Left && Magneto_Right) {
550 // cout << "Both On ";
551 } else if (Magneto_Left == 0 || Magneto_Right== 0) {
552 // cout << "1 Magneto Failed ";
554 Percentage_Power = Percentage_Power *
555 ((100.0 - Mag_Derate_Percent)/100.0);
556 // cout << FGEng1_Percentage_Power << "%" << "\t";
559 // Calculate Engine Horsepower
561 HP = Percentage_Power * MaxHP / 100.0;
563 Power_SI = HP * CONVERT_HP_TO_WATTS;
565 // Calculate Engine Torque
567 Torque = HP * 5252 / RPM;
568 // cout << Torque << "Ft/lbs" << "\t";
570 Torque_SI = (Power_SI * 60.0) / (2.0 * PI * RPM); //Torque = power / angular velocity
571 // cout << Torque << " Nm\n";
573 // Calculate Cylinder Head Temperature
574 CHT = Calc_CHT( Fuel_Flow, Mixture, IAS);
575 // cout << "Cylinder Head Temp (F) = " << CHT << endl;
577 // EGT = Calc_EGT( Mixture );
579 // Calculate Oil Pressure
580 Oil_Pressure = Oil_Press( Oil_Temp, RPM );
581 // cout << "Oil Pressure (PSI) = " << Oil_Pressure << endl;
583 //==============================================================
585 // Now do the Propellor Calculations
587 #ifdef PHILS_PROP_MODEL
590 FGProp1_RPS = RPM * Gear_Ratio / 60.0;
591 // cout << FGProp1_RPS << " RPS" << endl;
593 //Radial Flow Vector (V2) Ft/sec at Ref Blade Station (usually 30")
594 FGProp1_Angular_V = FGProp1_RPS * 2 * PI * (Blade_Station / 12);
595 // cout << FGProp1_Angular_V << "Angular Velocity " << endl;
597 // Axial Flow Vector (Vo) Ft/sec
598 // Some further work required here to allow for inflow at low speeds
599 // Vo = (IAS + 20) * 1.688888;
600 Vo = IAS_to_FPS(IAS + 20);
601 // cout << "Feet/sec = " << Vo << endl;
603 // cout << Vo << "Axial Velocity" << endl;
605 // Relative Velocity (V1)
606 V1 = sqrt((FGProp1_Angular_V * FGProp1_Angular_V) +
608 // cout << V1 << "Relative Velocity " << endl;
610 // cout << FGProp1_Blade_Angle << " Prop Blade Angle" << endl;
612 // Blade Angle of Attack (Alpha1)
614 /* cout << " Alpha1 = " << Alpha1
615 << " Blade angle = " << FGProp1_Blade_Angle
617 << " FGProp1_Angular_V = " << FGProp1_Angular_V << endl;*/
618 Alpha1 = FGProp1_Blade_Angle -(atan(Vo / FGProp1_Angular_V) * (180/PI));
619 // cout << Alpha1 << " Alpha1" << endl;
621 // Calculate Coefficient of Drag at Alpha1
622 FGProp1_Coef_Drag = (0.0005 * (Alpha1 * Alpha1)) + (0.0003 * Alpha1)
624 // cout << FGProp1_Coef_Drag << " Coef Drag" << endl;
626 // Calculate Coefficient of Lift at Alpha1
627 FGProp1_Coef_Lift = -(0.0026 * (Alpha1 * Alpha1)) + (0.1027 * Alpha1)
629 // cout << FGProp1_Coef_Lift << " Coef Lift " << endl;
631 // Covert Alplha1 to Radians
632 // Alpha1 = Alpha1 * PI / 180;
634 // Calculate Prop Torque
635 FGProp1_Torque = (0.5 * Rho * (V1 * V1) * FGProp_Area
636 * ((FGProp1_Coef_Lift * sin(Alpha1 * PI / 180))
637 + (FGProp1_Coef_Drag * cos(Alpha1 * PI / 180))))
638 * (Blade_Station/12);
639 // cout << FGProp1_Torque << " Prop Torque" << endl;
641 // Calculate Prop Thrust
642 // cout << " V1 = " << V1 << " Alpha1 = " << Alpha1 << endl;
643 FGProp1_Thrust = 0.5 * Rho * (V1 * V1) * FGProp_Area
644 * ((FGProp1_Coef_Lift * cos(Alpha1 * PI / 180))
645 - (FGProp1_Coef_Drag * sin(Alpha1 * PI / 180)));
646 // cout << FGProp1_Thrust << " Prop Thrust " << endl;
648 // End of Propeller Calculations
649 //==============================================================
651 #endif //PHILS_PROP_MODEL
653 #ifdef NEVS_PROP_MODEL
658 number_of_blades = 2.0;
660 allowance_for_spinner = blade_length / 12.0;
661 prop_fudge_factor = 1.453401525;
662 forward_velocity = IAS;
671 angular_velocity_SI = 2.0 * PI * RPM / 60.0;
673 allowance_for_spinner = blade_length / 12.0;
674 //Calculate thrust and torque by summing the contributions from each of the blade elements
675 //Assumes equal length elements with numbered 1 inboard -> num_elements outboard
679 // outfile << "Rho = " << Rho << '\n\n';
680 // outfile << "Drag = ";
681 for(i=1;i<=num_elements;i++)
684 distance = (blade_length * (element / num_elements)) + allowance_for_spinner;
685 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))))))
686 * (0.1 * (blade_length / element)) * number_of_blades;
688 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)
689 * (0.1 * (blade_length / element)) * number_of_blades;
690 element_torque = element_drag * distance;
691 prop_torque += element_torque;
692 prop_thrust += element_lift;
693 // outfile << "Drag = " << element_drag << " n = " << element << '\n';
698 // outfile << "Angular velocity = " << angular_velocity_SI << " rad/s\n";
700 // cout << "Thrust = " << prop_thrust << '\n';
701 prop_thrust *= prop_fudge_factor;
702 prop_torque *= prop_fudge_factor;
703 prop_power_consumed_SI = prop_torque * angular_velocity_SI;
704 prop_power_consumed_HP = prop_power_consumed_SI / 745.699;
707 #endif //NEVS_PROP_MODEL
711 #ifdef PHILS_PROP_MODEL //Do Torque calculations in Ft/lbs - yuk :-(((
712 Torque_Imbalance = FGProp1_Torque - Torque;
715 #ifdef NEVS_PROP_MODEL //use proper units - Nm
716 Torque_Imbalance = prop_torque - Torque_SI;
719 // cout << Torque_Imbalance << endl;
721 // Some really crude engine speed calculations for now - we really need some moments of inertia and a dt in here !!!!
722 if (Torque_Imbalance > 5) {
724 // FGProp1_RPM -= 25;
725 // FGProp1_Blade_Angle -= 0.75;
728 if (Torque_Imbalance < -5) {
730 // FGProp1_RPM += 25;
731 // FGProp1_Blade_Angle += 0.75;
734 //DCL - This constant speed prop bit is all a bit of a hack for now
736 if( RPM > (Desired_RPM + 2)) {
737 FGProp1_Blade_Angle += 0.75; //This value could be altered depending on how far from the desired RPM we are
740 if( RPM < (Desired_RPM - 2)) {
741 FGProp1_Blade_Angle -= 0.75;
744 if (FGProp1_Blade_Angle < FGProp_Fine_Pitch_Stop) {
745 FGProp1_Blade_Angle = FGProp_Fine_Pitch_Stop;
752 //end constant speed prop
755 //DCL - stall the engine if RPM drops below 550 - this is possible if mixture lever is pulled right out
759 // outfile << "RPM = " << RPM << " Blade angle = " << FGProp1_Blade_Angle << " Engine torque = " << Torque << " Prop torque = " << FGProp1_Torque << '\n';
760 outfile << "RPM = " << RPM << " Engine torque = " << Torque_SI << " Prop torque = " << prop_torque << '\n';
762 // cout << FGEng1_RPM << " Blade_Angle " << FGProp1_Blade_Angle << endl << endl;
766 // cout << "Final engine RPM = " << RPM << '\n';
774 // Calculate Oil Temperature
776 static float Oil_Temp (float Fuel_Flow, float Mixture, float IAS)