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Correct calculatePressureDrag() to iterate through all instances.

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This commit is contained in:
JoePfeiffer 2020-03-19 11:13:40 -06:00
parent 5483c3e659
commit 05185ff3d6
2 changed files with 34 additions and 27 deletions
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59
core/src/net/sf/openrocket/aerodynamics/BarrowmanCalculator.java
View File

@ -402,7 +402,7 @@ public class BarrowmanCalculator extends AbstractAerodynamicCalculator {
!(c instanceof FinSet))
continue;
// iterate across component instances
// iterate across component instances
final ArrayList<InstanceContext> contextList = entry.getValue();
for(InstanceContext context: contextList ) {
@ -515,39 +515,46 @@ public class BarrowmanCalculator extends AbstractAerodynamicCalculator {
base = calculateBaseCD(conditions.getMach());
total = 0;
for (RocketComponent c : configuration.getActiveComponents()) {
final InstanceMap imap = configuration.getActiveInstances();
for(Map.Entry<RocketComponent, ArrayList<InstanceContext>> entry: imap.entrySet() ) {
final RocketComponent c = entry.getKey();
if (!c.isAerodynamic())
continue;
// Pressure fore drag
double cd = calcMap.get(c).calculatePressureDragForce(conditions, stagnation, base,
warnings);
total += cd;
if (map != null) {
map.get(c).setPressureCD(cd);
}
if(c.isCDOverridden()) continue;
// Stagnation drag
if (c instanceof SymmetricComponent) {
SymmetricComponent s = (SymmetricComponent) c;
// iterate across component instances
final ArrayList<InstanceContext> contextList = entry.getValue();
for(InstanceContext context: contextList ) {
if (radius < s.getForeRadius()) {
double area = Math.PI * (pow2(s.getForeRadius()) - pow2(radius));
cd = stagnation * area / conditions.getRefArea();
total += cd;
if (map != null) {
map.get(c).setPressureCD(map.get(c).getPressureCD() + cd);
}
// Pressure fore drag
double cd = calcMap.get(c).calculatePressureDragForce(conditions, stagnation, base,
warnings);
total += cd;
if (map != null) {
map.get(c).setPressureCD(cd);
}
radius = s.getAftRadius();
if(c.isCDOverridden()) continue;
// Stagnation drag
if (c instanceof SymmetricComponent) {
SymmetricComponent s = (SymmetricComponent) c;
if (radius < s.getForeRadius()) {
double area = Math.PI * (pow2(s.getForeRadius()) - pow2(radius));
cd = stagnation * area / conditions.getRefArea();
total += cd;
if (map != null) {
map.get(c).setPressureCD(map.get(c).getPressureCD() + cd);
}
}
radius = s.getAftRadius();
}
}
}
return total;
}

2
core/src/net/sf/openrocket/aerodynamics/barrowman/FinSetCalc.java
View File

@ -645,7 +645,7 @@ public class FinSetCalc extends RocketComponentCalc {
// Airfoil assumed to have zero base drag
// Scale to correct reference area
drag *= finCount * span * thickness / conditions.getRefArea();
drag *= span * thickness / conditions.getRefArea();
return drag;
}