git.gag.com Git - debian/openrocket/blob - src/net/sf/openrocket/aerodynamics/AerodynamicForces.java

   1 package net.sf.openrocket.aerodynamics;
   2
   3 import net.sf.openrocket.rocketcomponent.RocketComponent;
   4 import net.sf.openrocket.util.BugException;
   5 import net.sf.openrocket.util.Coordinate;
   6
   7 public class AerodynamicForces implements Cloneable {
   8
   9         /**
  10          * The component this data is referring to.  Used in analysis methods.
  11          * A total value is indicated by the component being the Rocket component.
  12          */
  13         public RocketComponent component = null;
  14
  15
  16         /** CG and mass */
  17         public Coordinate cg = null;
  18
  19         /** Longitudal moment of inertia with reference to the CG. */
  20         public double longitudalInertia = Double.NaN;
  21
  22         /** Rotational moment of inertia with reference to the CG. */
  23         public double rotationalInertia = Double.NaN;
  24
  25
  26
  27         /** CP and CNa. */
  28         public Coordinate cp = null;
  29
  30
  31         /**
  32          * Normal force coefficient derivative.  At values close to zero angle of attack
  33          * this value may be poorly defined or NaN if the calculation method does not
  34          * compute CNa directly.
  35          */
  36         public double CNa = Double.NaN;
  37
  38
  39         /** Normal force coefficient. */
  40         public double CN = Double.NaN;
  41
  42         /** Pitching moment coefficient, relative to the coordinate origin. */
  43         public double Cm = Double.NaN;
  44
  45         /** Side force coefficient, Cy */
  46         public double Cside = Double.NaN;
  47
  48         /** Yaw moment coefficient, Cn, relative to the coordinate origin. */
  49         public double Cyaw = Double.NaN;
  50
  51         /** Roll moment coefficient, Cl, relative to the coordinate origin. */
  52         public double Croll = Double.NaN;
  53
  54         /** Roll moment damping coefficient */
  55         public double CrollDamp = Double.NaN;
  56
  57         /** Roll moment forcing coefficient */
  58         public double CrollForce = Double.NaN;
  59
  60
  61
  62         /** Axial drag coefficient, CA */
  63         public double Caxial = Double.NaN;
  64
  65         /** Total drag force coefficient, parallel to the airflow. */
  66         public double CD = Double.NaN;
  67
  68         /** Drag coefficient due to fore pressure drag. */
  69         public double pressureCD = Double.NaN;
  70
  71         /** Drag coefficient due to base drag. */
  72         public double baseCD = Double.NaN;
  73
  74         /** Drag coefficient due to friction drag. */
  75         public double frictionCD = Double.NaN;
  76
  77
  78         public double pitchDampingMoment = Double.NaN;
  79         public double yawDampingMoment = Double.NaN;
  80
  81
  82         /**
  83          * Reset all values to null/NaN.
  84          */
  85         public void reset() {
  86                 component = null;
  87                 cg = null;
  88                 longitudalInertia = Double.NaN;
  89                 rotationalInertia = Double.NaN;
  90
  91                 cp = null;
  92                 CNa = Double.NaN;
  93                 CN = Double.NaN;
  94                 Cm = Double.NaN;
  95                 Cside = Double.NaN;
  96                 Cyaw = Double.NaN;
  97                 Croll = Double.NaN;
  98                 CrollDamp = Double.NaN;
  99                 CrollForce = Double.NaN;
 100                 Caxial = Double.NaN;
 101                 CD = Double.NaN;
 102                 pitchDampingMoment = Double.NaN;
 103                 yawDampingMoment = Double.NaN;
 104         }
 105
 106         /**
 107          * Zero all values to 0 / Coordinate.NUL.  Component is left as it was.
 108          */
 109         public void zero() {
 110                 // component untouched
 111                 cg = Coordinate.NUL;
 112                 longitudalInertia = 0;
 113                 rotationalInertia = 0;
 114
 115                 cp = Coordinate.NUL;
 116                 CNa = 0;
 117                 CN = 0;
 118                 Cm = 0;
 119                 Cside = 0;
 120                 Cyaw = 0;
 121                 Croll = 0;
 122                 CrollDamp = 0;
 123                 CrollForce = 0;
 124                 Caxial = 0;
 125                 CD = 0;
 126                 pitchDampingMoment = 0;
 127                 yawDampingMoment = 0;
 128         }
 129
 130
 131         @Override
 132         public AerodynamicForces clone() {
 133                 try {
 134                         return (AerodynamicForces)super.clone();
 135                 } catch (CloneNotSupportedException e) {
 136                         throw new BugException("CloneNotSupportedException?!?");
 137                 }
 138         }
 139
 140         @Override
 141         public String toString() {
 142                 String text="AerodynamicForces[";
 143
 144                 if (component != null)
 145                         text += "component:" + component + ",";
 146                 if (cg != null)
 147                         text += "cg:" + cg + ",";
 148                 if (cp != null)
 149                         text += "cp:" + cp + ",";
 150                 if (!Double.isNaN(longitudalInertia))
 151                         text += "longIn:" + longitudalInertia + ",";
 152                 if (!Double.isNaN(rotationalInertia))
 153                         text += "rotIn:" + rotationalInertia + ",";
 154
 155                 if (!Double.isNaN(CNa))
 156                         text += "CNa:" + CNa + ",";
 157                 if (!Double.isNaN(CN))
 158                         text += "CN:" + CN + ",";
 159                 if (!Double.isNaN(Cm))
 160                         text += "Cm:" + Cm + ",";
 161
 162                 if (!Double.isNaN(Cside))
 163                         text += "Cside:" + Cside + ",";
 164                 if (!Double.isNaN(Cyaw))
 165                         text += "Cyaw:" + Cyaw + ",";
 166
 167                 if (!Double.isNaN(Croll))
 168                         text += "Croll:" + Croll + ",";
 169                 if (!Double.isNaN(Caxial))
 170                         text += "Caxial:" + Caxial + ",";
 171
 172                 if (!Double.isNaN(CD))
 173                         text += "CD:" + CD + ",";
 174
 175                 if (text.charAt(text.length()-1) == ',')
 176                         text = text.substring(0, text.length()-1);
 177
 178                 text += "]";
 179                 return text;
 180         }
 181 }