// INCLUDES
// ------------------------------------------------------------------------
-#include <iostream.h>
+#include <simgear/compiler.h>
+
+#include <iostream>
#include <math.h>
#include "10520d.hxx"
+SG_USING_STD(cout);
+SG_USING_STD(endl);
// ------------------------------------------------------------------------
// CODE
// 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);
+ float RPM = LeverPosition * (Max_RPM - Min_RPM) /100 + Min_RPM ;
if ( RPM >= Max_RPM ) {
RPM = Max_RPM;
// Initialise Engine Variables used by this instance
Percentage_Power = 0;
Manifold_Pressure = 29.00; // Inches
- RPM = 2700;
+ RPM = 500;
Fuel_Flow = 0; // lbs/hour
Torque = 0;
CHT = 370;
Alpha1 = 13.5;
FGProp1_Blade_Angle = 13.5;
FGProp_Fine_Pitch_Stop = 13.5;
+ FGProp_Course_Pitch_Stop = 55;
// Other internal values
Rho = 0.002378;
// Calculate Density Ratio
static float Density_Ratio ( float x )
{
- float y ;
- y = ((3E-10 * x * x) - (3E-05 * x) + 0.9998);
- return(y);
+ float 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);
+ float 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)
+static float IAS_to_FPS (float ias)
{
- float y;
- y = x * 1.68888888;
- return y;
+ return ias * 1.68888888;
}
// update the engine model based on current control positions
void FGEngine::update() {
// Declare local variables
- int num = 0;
- const int num2 = 1; // default is 100, number if iterations to run
+ int num = 0; // Not used. Counting variables
+ int num2 = 100; // Not used.
float ManXRPM = 0;
float Vo = 0;
float V1 = 0;
-
// Set up the new variables
float Blade_Station = 30;
+ float Rho = 0.002378;
float FGProp_Area = 1.405/3;
float PI = 3.1428571;
// Input Variables
+ // float IAS = 0;
// 0 = Closed, 100 = Fully Open
// float Throttle_Lever_Pos = 75;
// Environmental Variables
- // Temp Variation from ISA (Deg F)
+ // Temp Variation from ISA (Deg F)
float FG_ISA_VAR = 0;
// Pressure Altitude 1000's of Feet
float FG_Pressure_Ht = 0;
Manifold_Pressure =
Calc_Manifold_Pressure( Throttle_Lever_Pos, Max_Manifold_Pressure );
- // cout << "manifold pressure = " << Manifold_Pressure << endl;
+ cout << "manifold pressure = " << Manifold_Pressure << endl;
- // 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);
-
RPM = Calc_Engine_RPM(Propeller_Lever_Pos);
// cout << "Engine RPM = " << RPM << endl;
Desired_RPM = RPM;
+ cout << "Desired RPM = " << Desired_RPM << endl;
//==================================================================
// 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";
+ // cout << endl << "====================" << endl;
+ // cout << "MP Inches = " << Manifold_Pressure << "\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;
+ // cout << ManXRPM << endl;
// Calculate % Power
Percentage_Power = (+ 7E-09 * ManXRPM * ManXRPM)
+ ( + 7E-04 * ManXRPM) - 0.1218;
- // cout << Percentage_Power << "%" << "\t";
+ // cout << "percent power = " << 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";
+ // cout << " adjusted T = " << 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";
+ // cout << " adjusted A = " << Percentage_Power << "%" << "\t";
// Now Calculate Fuel Flow based on % Power Best Power Mixture
Fuel_Flow = Percentage_Power * Max_Fuel_Flow / 100.0;
Percentage_Power = Percentage_Power *
((100.0 - Mag_Derate_Percent)/100.0);
- // cout << FGEng1_Percentage_Power << "%" << "\t";
}
+ // cout << "Final engine % power = " << Percentage_Power << "%" << endl;
// Calculate Engine Horsepower
//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;
+ // cout << "Angular Velocity " << FGProp1_Angular_V << endl;
// Axial Flow Vector (Vo) Ft/sec
// Some further work required here to allow for inflow at low speeds
// Relative Velocity (V1)
V1 = sqrt((FGProp1_Angular_V * FGProp1_Angular_V) +
(Vo * Vo));
- // cout << V1 << "Relative Velocity " << endl;
+ // cout << "Relative Velocity " << V1 << endl;
+
+ if ( FGProp1_Blade_Angle >= FGProp_Course_Pitch_Stop ) {
+ FGProp1_Blade_Angle = FGProp_Course_Pitch_Stop;
+ }
// 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;
+ // cout << " Alpha1 = " << Alpha1
+ // << " Blade angle = " << FGProp1_Blade_Angle
+ // << " Vo = " << Vo
+ // << " FGProp1_Angular_V = " << FGProp1_Angular_V << endl;
+
// Calculate Coefficient of Drag at Alpha1
FGProp1_Coef_Drag = (0.0005 * (Alpha1 * Alpha1)) + (0.0003 * Alpha1)
+ 0.0094;
* ((FGProp1_Coef_Lift * sin(Alpha1 * PI / 180))
+ (FGProp1_Coef_Drag * cos(Alpha1 * PI / 180))))
* (Blade_Station/12);
- // cout << FGProp1_Torque << " Prop Torque" << endl;
+ // cout << "Prop Torque = " << FGProp1_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;
+ // cout << " Prop Thrust = " << FGProp1_Thrust << endl;
// End of Propeller Calculations
//==============================================================
-#if 0
Torque_Imbalance = FGProp1_Torque - Torque;
// cout << Torque_Imbalance << endl;
if (RPM >= 2700) {
RPM = 2700;
}
-#endif
// cout << FGEng1_RPM << " Blade_Angle " << FGProp1_Blade_Angle << endl << endl;
projects / flightgear.git / blobdiff