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removed commented sysout lines

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This commit is contained in:
Sampo Niskanen 2011-09-04 17:52:21 +00:00
parent 38426ff0fc
commit 950dd49561
1 changed files with 2 additions and 37 deletions
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35
src/net/sf/openrocket/aerodynamics/BarrowmanCalculator.java
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@ -206,7 +206,6 @@ public class BarrowmanCalculator extends AbstractAerodynamicCalculator {
calcMap.get(component).calculateNonaxialForces(conditions, forces, warnings); calcMap.get(component).calculateNonaxialForces(conditions, forces, warnings);
forces.setCP(component.toAbsolute(forces.getCP())[0]); forces.setCP(component.toAbsolute(forces.getCP())[0]);
forces.setCm(forces.getCN() * forces.getCP().x / conditions.getRefLength()); forces.setCm(forces.getCN() * forces.getCP().x / conditions.getRefLength());
// System.out.println(" CN="+forces.CN+" cp.x="+forces.cp.x+" Cm="+forces.Cm);
if (map != null) { if (map != null) {
AerodynamicForces f = map.get(component); AerodynamicForces f = map.get(component);
@ -256,25 +255,19 @@ public class BarrowmanCalculator extends AbstractAerodynamicCalculator {
Re = conditions.getVelocity() * configuration.getLength() / Re = conditions.getVelocity() * configuration.getLength() /
conditions.getAtmosphericConditions().getKinematicViscosity(); conditions.getAtmosphericConditions().getKinematicViscosity();
// System.out.printf("Re=%.3e ", Re);
// Calculate the skin friction coefficient (assume non-roughness limited) // Calculate the skin friction coefficient (assume non-roughness limited)
if (configuration.getRocket().isPerfectFinish()) { if (configuration.getRocket().isPerfectFinish()) {
// System.out.printf("Perfect finish: Re=%f ",Re);
// Assume partial laminar layer. Roughness-limitation is checked later. // Assume partial laminar layer. Roughness-limitation is checked later.
if (Re < 1e4) { if (Re < 1e4) {
// Too low, constant // Too low, constant
Cf = 1.33e-2; Cf = 1.33e-2;
// System.out.printf("constant Cf=%f ",Cf);
} else if (Re < 5.39e5) { } else if (Re < 5.39e5) {
// Fully laminar // Fully laminar
Cf = 1.328 / MathUtil.safeSqrt(Re); Cf = 1.328 / MathUtil.safeSqrt(Re);
// System.out.printf("basic Cf=%f ",Cf);
} else { } else {
// Transitional // Transitional
Cf = 1.0 / pow2(1.50 * Math.log(Re) - 5.6) - 1700 / Re; Cf = 1.0 / pow2(1.50 * Math.log(Re) - 5.6) - 1700 / Re;
// System.out.printf("transitional Cf=%f ",Cf);
} }
// Compressibility correction // Compressibility correction
@ -299,7 +292,6 @@ public class BarrowmanCalculator extends AbstractAerodynamicCalculator {
} }
} }
// System.out.printf("c1=%f c2=%f\n", c1,c2);
// Applying continuously around Mach 1 // Applying continuously around Mach 1
if (mach < 0.9) { if (mach < 0.9) {
Cf *= c1; Cf *= c1;
@ -309,7 +301,6 @@ public class BarrowmanCalculator extends AbstractAerodynamicCalculator {
Cf *= c2; Cf *= c2;
} }
// System.out.printf("M=%f Cf=%f (smooth)\n",mach,Cf);
} else { } else {
@ -317,11 +308,9 @@ public class BarrowmanCalculator extends AbstractAerodynamicCalculator {
if (Re < 1e4) { if (Re < 1e4) {
// Too low, constant // Too low, constant
Cf = 1.48e-2; Cf = 1.48e-2;
// System.out.printf("LOW-TURB ");
} else { } else {
// Turbulent // Turbulent
Cf = 1.0 / pow2(1.50 * Math.log(Re) - 5.6); Cf = 1.0 / pow2(1.50 * Math.log(Re) - 5.6);
// System.out.printf("NORMAL-TURB ");
} }
// Compressibility correction // Compressibility correction
@ -341,8 +330,6 @@ public class BarrowmanCalculator extends AbstractAerodynamicCalculator {
Cf *= c2; Cf *= c2;
} }
// System.out.printf("M=%f, Cd=%f (turbulent)\n", mach,Cf);
} }
// Roughness-limited value correction term // Roughness-limited value correction term
@ -357,7 +344,6 @@ public class BarrowmanCalculator extends AbstractAerodynamicCalculator {
roughnessCorrection = c2 * (mach - 0.9) / 0.2 + c1 * (1.1 - mach) / 0.2; roughnessCorrection = c2 * (mach - 0.9) / 0.2 + c1 * (1.1 - mach) / 0.2;
} }
// System.out.printf("Cf=%.3f ", Cf);
/* /*
@ -388,9 +374,6 @@ public class BarrowmanCalculator extends AbstractAerodynamicCalculator {
roughnessLimited[finish.ordinal()] = roughnessLimited[finish.ordinal()] =
0.032 * Math.pow(finish.getRoughnessSize() / configuration.getLength(), 0.2) * 0.032 * Math.pow(finish.getRoughnessSize() / configuration.getLength(), 0.2) *
roughnessCorrection; roughnessCorrection;
// System.out.printf("roughness["+finish+"]=%.3f ",
// roughnessLimited[finish.ordinal()]);
} }
/* /*
@ -403,14 +386,8 @@ public class BarrowmanCalculator extends AbstractAerodynamicCalculator {
// For perfect finish require Re > 1e6 // For perfect finish require Re > 1e6
if ((Re > 1.0e6) && (roughnessLimited[finish.ordinal()] > Cf)) { if ((Re > 1.0e6) && (roughnessLimited[finish.ordinal()] > Cf)) {
componentCf = roughnessLimited[finish.ordinal()]; componentCf = roughnessLimited[finish.ordinal()];
// System.out.printf(" rl=%f Cf=%f (perfect=%b)\n",
// roughnessLimited[finish.ordinal()],
// Cf,rocket.isPerfectFinish());
// System.out.printf("LIMITED ");
} else { } else {
componentCf = Cf; componentCf = Cf;
// System.out.printf("NORMAL ");
} }
} else { } else {
@ -420,9 +397,6 @@ public class BarrowmanCalculator extends AbstractAerodynamicCalculator {
} }
// System.out.printf("compCf=%.3f ", componentCf);
// Calculate the friction drag: // Calculate the friction drag:
@ -471,7 +445,6 @@ public class BarrowmanCalculator extends AbstractAerodynamicCalculator {
} }
} }
// System.out.printf("\n");
return (finFriction + correction * bodyFriction) / conditions.getRefArea(); return (finFriction + correction * bodyFriction) / conditions.getRefArea();
} }
@ -651,16 +624,8 @@ public class BarrowmanCalculator extends AbstractAerodynamicCalculator {
vel = MathUtil.max(vel, 1); vel = MathUtil.max(vel, 1);
// double Cm = total.Cm - total.CN * total.cg.x / conditions.getRefLength();
// System.out.printf("Damping pitch/yaw, mul=%.4f pitch rate=%.4f "+
// "Cm=%.4f / %.4f effect=%.4f aoa=%.4f\n", mul, pitch, total.Cm, Cm,
// -(mul * MathUtil.sign(pitch) * pow2(pitch/vel)),
// conditions.getAOA()*180/Math.PI);
mul *= 3; // TODO: Higher damping yields much more realistic apogee turn mul *= 3; // TODO: Higher damping yields much more realistic apogee turn
// total.Cm -= mul * pitch / pow2(vel);
// total.Cyaw -= mul * yaw / pow2(vel);
total.setPitchDampingMoment(mul * MathUtil.sign(pitch) * pow2(pitch / vel)); total.setPitchDampingMoment(mul * MathUtil.sign(pitch) * pow2(pitch / vel));
total.setYawDampingMoment(mul * MathUtil.sign(yaw) * pow2(yaw / vel)); total.setYawDampingMoment(mul * MathUtil.sign(yaw) * pow2(yaw / vel));
} }