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Remove debug prints

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This commit is contained in:
SiboVG 2024-10-08 19:05:18 +02:00
parent e51790e69d
commit ab5fa61d3e
1 changed files with 3 additions and 26 deletions
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29
core/src/main/java/info/openrocket/core/aerodynamics/barrowman/FinSetCalc.java
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@ -162,9 +162,6 @@ public class FinSetCalc extends RocketComponentCalc {
// TODO: LOW: fin-fin mach cone effect, MIL-HDBK page 5-25
// Calculate CP position
double x = macLead + calculateCPPos(conditions) * macLength;
// logger.debug("Component macLead = {}", macLead);
// logger.debug("Component macLength = {}", macLength);
// logger.debug("Component x = {}", x);
// Calculate roll forces, reduce forcing above stall angle
@ -176,17 +173,12 @@ public class FinSetCalc extends RocketComponentCalc {
forces.setCrollForce((macSpan + r) * cna1 * (1 + tau) * cantAngle / conditions.getRefLength());
if (conditions.getAOA() > STALL_ANGLE) {
// System.out.println("Fin stalling in roll");
forces.setCrollForce(forces.getCrollForce() * MathUtil.clamp(
1 - (conditions.getAOA() - STALL_ANGLE) / (STALL_ANGLE / 2), 0, 1));
}
forces.setCrollDamp(calculateDampingMoment(conditions));
forces.setCroll(forces.getCrollForce() - forces.getCrollDamp());
// System.out.printf(component.getName() + ": roll rate:%.3f force:%.3f damp:%.3f " +
// "total:%.3f\n",
// conditions.getRollRate(), forces.CrollForce, forces.CrollDamp, forces.Croll);
forces.setCNa(cna);
forces.setCN(cna * MathUtil.min(conditions.getAOA(), STALL_ANGLE));
forces.setCP(new Coordinate(x, 0, 0, cna));
@ -349,7 +341,6 @@ public class FinSetCalc extends RocketComponentCalc {
double y = i * dy;
macLength += length * length;
//logger.debug("macLength = {}, length = {}, i = {}", macLength, length, i);
macSpan += y * length;
macLead += chordLead[i] * length;
area += length;
@ -408,10 +399,6 @@ public class FinSetCalc extends RocketComponentCalc {
K1 = new LinearInterpolator(x, k1);
K2 = new LinearInterpolator(x, k2);
K3 = new LinearInterpolator(x, k3);
// System.out.println("K1[m="+CNA_SUPERSONIC+"] = "+k1[0]);
// System.out.println("K2[m="+CNA_SUPERSONIC+"] = "+k2[0]);
// System.out.println("K3[m="+CNA_SUPERSONIC+"] = "+k3[0]);
}
protected double calculateFinCNa1(FlightConditions conditions) {
@ -445,8 +432,6 @@ public class FinSetCalc extends RocketComponentCalc {
K3.getValue(CNA_SUPERSONIC) * pow2(alpha)) / ref;
superD = -finArea / ref * 2 * CNA_SUPERSONIC / CNA_SUPERSONIC_B;
// System.out.println("subV="+subV+" superV="+superV+" subD="+subD+" superD="+superD);
return cnaInterpolator.interpolate(mach, subV, superV, subD, superD, 0);
}
@ -473,18 +458,11 @@ public class FinSetCalc extends RocketComponentCalc {
}
sum = sum * (span / DIVISIONS) * 2 * Math.PI / conditions.getBeta() /
(conditions.getRefArea() * conditions.getRefLength());
// System.out.println("SPECIAL: " +
// (MathUtil.sign(rollRate) * sum));
return MathUtil.sign(rollRate) * sum;
}
if (mach <= CNA_SUBSONIC) {
// System.out.println("BASIC: "+
// (2*Math.PI * rollRate * rollSum /
// (conditions.getRefArea() * conditions.getRefLength() *
// conditions.getVelocity() * conditions.getBeta())));
return 2 * Math.PI * rollRate * rollSum /
(conditions.getRefArea() * conditions.getRefLength() *
conditions.getVelocity() * conditions.getBeta());
@ -511,7 +489,6 @@ public class FinSetCalc extends RocketComponentCalc {
}
// Transonic, do linear interpolation
FlightConditions cond = conditions.clone();
cond.setMach(CNA_SUBSONIC - 0.01);
double subsonic = calculateDampingMoment(cond);
@ -532,7 +509,7 @@ public class FinSetCalc extends RocketComponentCalc {
*/
private double calculateCPPos(FlightConditions cond) {
double m = cond.getMach();
// logger.debug("m = {} ", m);
if (m <= 0.5) {
// At subsonic speeds CP at quarter chord
return 0.25;
@ -551,7 +528,7 @@ public class FinSetCalc extends RocketComponentCalc {
val += v * x;
x *= m;
}
// logger.debug("val = {}", val);
return val;
}