RealFuels.SolverRF.CalculatePerformance C# (CSharp) Method

        public override void CalculatePerformance(double airRatio, double commandedThrottle, double flowMult, double ispMult)
        {
            // set base bits
            base.CalculatePerformance(airRatio, commandedThrottle, flowMult, ispMult);
            M0 = mach;

            // Calculate Isp (before the shutdown check, so it displays even then)
            Isp = atmosphereCurve.Evaluate((float)(p0 * 0.001d * PhysicsGlobals.KpaToAtmospheres)) * ispMult;

            // if we're not combusting, don't combust and start cooling off
            combusting = running;
            statusString = "Nominal";

            // ullage check first, overwrite if bad pressure or no propellants
            if (!ullage)
            {
                combusting = false;
                statusString = "Vapor in feed line";
            }

            // check fuel flow fraction
            if (ffFraction <= 0d)
            {
                combusting = false;
                statusString = "No propellants";
            }
            // check pressure
            if (!pressure)
            {
                combusting = false;
                statusString = "Lack of pressure";
            }

            if (disableUnderwater && underwater)
            {
                combusting = false;
                statusString = "Underwater";
            }

            // check flow mult
            double fuelFlowMult = FlowMult();
            if (fuelFlowMult < flowMultMin)
            {
                combusting = false;
                statusString = "Airflow outside specs";
            }

            if (commandedThrottle <= 0d)
                combusting = false;

            if (!combusting)
            {
                double declinePow = Math.Pow(tempDeclineRate, TimeWarp.fixedDeltaTime);
                chamberTemp = Math.Max(Math.Max(t0, partTemperature), chamberTemp * declinePow);
                fxPower = 0f;
            }
            else
            {

                // get current flow, and thus thrust.
                fuelFlow = scale * flowMult * maxFlow * commandedThrottle * thrustRatio;

                if (varyThrust > 0d && fuelFlow > 0d && HighLogic.LoadedSceneIsFlight)
                    fuelFlow *= (1d + (Mathf.PerlinNoise(Time.time, 0f) * 2d - 1d) * varyThrust);

                fxPower = (float)(fuelFlow * maxFlowRecip * ispMult); // FX is proportional to fuel flow and Isp mult.

                // apply fuel flow multiplier
                double ffMult = fuelFlow * fuelFlowMult;
                fuelFlow = ffMult;

                if(atmCurveIsp != null)
                    Isp *= atmCurveIsp.Evaluate((float)(rho * (1d / 1.225d)));
                if (velCurveIsp != null)
                    Isp *= velCurveIsp.Evaluate((float)mach);

                double exhaustVelocity = Isp * 9.80665d;
                SFC = 3600d / Isp;

                thrust = ffMult * exhaustVelocity; // either way, thrust is base * mult * EV

                // Calculate chamber temperature as ratio
                double desiredTempRatio = Math.Max(tempMin, fxPower);
                double machTemp = MachTemp() * 0.05d;
                desiredTempRatio = desiredTempRatio * (1d + machTemp) + machTemp;

                // set temp based on desired
                double desiredTemp = desiredTempRatio * chamberNominalTemp;
                if (Math.Abs(desiredTemp - chamberTemp) < 1d)
                    chamberTemp = desiredTemp;
                else
                {
                    double lerpVal = UtilMath.Clamp01(tempLerpRate * TimeWarp.fixedDeltaTime);
                    chamberTemp = UtilMath.LerpUnclamped(chamberTemp, desiredTemp, lerpVal);
                }
            }
            fxThrottle = combusting ? (float)throttle : 0f;
        }