public abstract class AeroCoefficients
extends java.lang.Object
implements java.io.Serializable, java.lang.Cloneable
Modified by: Joseph A. Huwaldt
Modifier and Type | Field and Description |
---|---|
protected double |
alpha
Flow angles used to transform between axis systems.
|
protected double |
beta
Flow angles used to transform between axis systems.
|
protected double |
CA
Body axes force coefficients.
|
protected double |
Clb
Body axes moment coefficients.
|
protected double |
CMb
Body axes moment coefficients.
|
protected double |
CN
Body axes force coefficients.
|
protected double |
Cnb
Body axes moment coefficients.
|
protected double |
CYb
Body axes force coefficients.
|
protected double |
phi
Flow angles used to transform between axis systems.
|
protected AeroReference |
ref
Aerodynamic reference quantities are stored here.
|
Modifier | Constructor and Description |
---|---|
protected |
AeroCoefficients()
Creates an AeroCoefficients object with all the coefficients
set to zero and with no reference quantities defined.
|
protected |
AeroCoefficients(AeroReference refValues)
Creates an AeroCoefficients object with all the coefficients
set to zero and the aero reference quantities set to
the given values.
|
protected |
AeroCoefficients(AeroReference refValues,
double CN,
double CA,
double CYb,
double CMb,
double Cnb,
double Clb)
Creates an AeroCoefficients object with the coefficients
and reference quantities as specified.
|
Modifier and Type | Method and Description |
---|---|
abstract void |
add(AeroCoefficients B)
Add the given aero coefficients to those contained in this
object.
|
void |
addCA(double delta)
Add the given increment to the current value of the body
axis axial force coefficient.
|
void |
addClb(double delta)
Add the given increment to the current value of the
body axis rolling moment coefficient.
|
void |
addCMb(double delta)
Add the given increment to the current value of the
body axis pitching moment coefficient.
|
void |
addCN(double delta)
Add the given increment to the current value of the body
axis normal force coefficient.
|
void |
addCnb(double delta)
Add the given increment to the current value of the
body axis yawing moment coefficient.
|
void |
addCYb(double delta)
Add the given increment to the current value of the body
axis side force coefficient.
|
abstract void |
changeRef(AeroReference newReference)
Change the reference quantities used by this set of aero
coefficients to those given.
|
java.lang.Object |
clone()
Make a copy of this AeroCoefficients object.
|
boolean |
equals(java.lang.Object obj)
Returns true if the input AeroCoefficients object has the same
numerical values (same reference quantities, and same body axis
coefficient values) as this one.
|
double |
getAOA()
Get the angle of attack used for resolving body axis
coefficients to wind and stability axes and back again.
|
double |
getCA()
Get the body axis axial force coefficient.
|
double |
getCD()
Get the wind axis drag force coefficient.
|
double |
getCDSA()
Get the stability axis drag force coefficient.
|
double |
getCl()
Get the wind axis rolling moment coefficient.
|
double |
getCL()
Get the wind axis lift force coefficient.
|
double |
getClb()
Get the body axis rolling moment coefficient.
|
double |
getClSA()
Get the stability axis rolling moment coefficient.
|
double |
getCLSA()
Get the stability axis lift force coefficient.
|
double |
getCM()
Get the wind axis pitching moment coefficient.
|
double |
getCMb()
Get the body axis pitching moment coefficient.
|
double |
getCMSA()
Get the stability axis pitching moment coefficient.
|
double |
getCn()
Get the wind axis yawing moment coefficient.
|
double |
getCN()
Get the body axis normal force coefficient.
|
double |
getCnb()
Get the body axis yawing moment coefficient.
|
double |
getCnSA()
Get the stability axis yawing moment coefficient.
|
double |
getCY()
Get the wind axis side force coefficient (CY).
|
double |
getCYb()
Get the body axis side force coefficient.
|
double |
getCYSA()
Get the stability axis side force coefficient (CYSA).
|
AeroReference |
getRef()
Return the reference quantities used by this set of aero
coefficients.
|
double |
getRoll()
Get the roll angle used for resolving body axis
coefficients to wind and stability axes and back again.
|
double |
getSideslip()
Get the sideslip angle used for resolving body axis
coefficients to wind and stability axes and back again.
|
int |
hashCode()
Returns a hash code value for the object.
|
void |
setAngles(double AOA,
double sideslip,
double roll)
Set the free stream flow angles used to resolve body axis
coefficients to wind and stability axes and vis-versa.
|
void |
setAOA(double value)
Set the angle of attack used for resolving body axis
coefficients to wind and stability axes and back again.
|
void |
setBodyAxesForces(double CN,
double CA,
double CYb)
Set the body axis force coefficients.
|
void |
setBodyAxesMoments(double CMb,
double Cnb,
double Clb)
Set the body axis moment coefficients.
|
void |
setCA(double value)
Set the body axis axial force coefficient.
|
void |
setClb(double value)
Set the body axis rolling moment coefficient.
|
void |
setCMb(double value)
Set the body axis pitching moment coefficient.
|
void |
setCN(double value)
Set the body axis normal force coefficient.
|
void |
setCnb(double value)
Set the body axis yawing moment coefficient.
|
void |
setCYb(double value)
Set the body axis side force coefficient.
|
void |
setRoll(double value)
Set the roll angle used for resolving body axis
coefficients to wind and stability axes and back again.
|
void |
setSideslip(double value)
Set the sideslip angle used for resolving body axis
coefficients to wind and stability axes and back again.
|
void |
setStabilityAxesForces(double CLSA,
double CDSA,
double CYSA)
Set the stability axis force coefficients.
|
void |
setStabilityAxesMoments(double CMSA,
double CnSA,
double ClSA)
Set the stability axis moment coefficients.
|
void |
setWindAxesForces(double CL,
double CD,
double CY)
Set the wind axis force coefficients.
|
void |
setWindAxesMoments(double CM,
double Cn,
double Cl)
Set the wind axis moment coefficients.
|
abstract void |
subtract(AeroCoefficients B)
Subtract the given aero coefficients from those contained in
object.
|
protected AeroReference ref
protected double CN
protected double CA
protected double CYb
protected double CMb
protected double Cnb
protected double Clb
protected double alpha
protected double beta
protected double phi
protected AeroCoefficients()
protected AeroCoefficients(AeroReference refValues)
refValues
- Aero reference quantities (ref area, span, etc).protected AeroCoefficients(AeroReference refValues, double CN, double CA, double CYb, double CMb, double Cnb, double Clb)
refValues
- Aero reference quantities (ref area, span, etc).CN
- Body axis normal force coefficient.CA
- Body axis axial force coefficient.CYb
- Body axis side force coefficient.CMb
- Body axis pitching moment coefficient at MRC.Cnb
- Body axis yawing moment coefficient at MRC.Clb
- Body axis rolling moment coefficient at MRC.public abstract void changeRef(AeroReference newReference)
newReference
- New reference quantities to scale this
object's aero coefficients to.public AeroReference getRef()
public abstract void add(AeroCoefficients B)
B
- The aero coefficients to be added to this object's
aero coefficients (this = this + B).public abstract void subtract(AeroCoefficients B)
B
- The aero coefficients to be subtracted from this
object's aero coefficients (this = this - B).public boolean equals(java.lang.Object obj)
equals
in class java.lang.Object
obj
- The AeroCoefficients object we are comparing this one to.public int hashCode()
hashCode
in class java.lang.Object
public java.lang.Object clone()
clone
in class java.lang.Object
public void setBodyAxesForces(double CN, double CA, double CYb)
CN
- Body axis normal force coefficient.CA
- Body axis axial force coefficient.CYb
- Body axis side force coefficient.public void setCN(double value)
value
- Normal force coefficient.public void setCA(double value)
value
- Axial force coefficient.public void setCYb(double value)
value
- Side force coefficient.public void setBodyAxesMoments(double CMb, double Cnb, double Clb)
CMb
- Body axis pitching moment coefficient.Cnb
- Body axis yawing moment coefficient.Clb
- Body axis rolling moment coefficient.public void setCMb(double value)
value
- Body axis pitching moment coefficient at the moment reference
center.public void setCnb(double value)
value
- Body axis yawing moment coefficient at the moment reference
center.public void setClb(double value)
value
- Body axis rolling moment coefficient at the moment reference
center.public double getCN()
public double getCA()
public double getCYb()
public double getCMb()
public double getCnb()
public double getClb()
public void addCN(double delta)
delta
- The amount to increase the body axis normal
force coefficient by.public void addCA(double delta)
delta
- The amount to increase the body axis axial
force coefficient by.public void addCYb(double delta)
delta
- The amount to increase the body axis side
force coefficient by.public void addCMb(double delta)
delta
- The amount to increase the pitching moment
coefficient by.public void addCnb(double delta)
delta
- The amount to increase the yawing moment
coefficient by.public void addClb(double delta)
delta
- The amount to increase the rolling moment
coefficient by.public void setAngles(double AOA, double sideslip, double roll)
AOA
- Angle of attack in radians.sideslip
- Sideslip angle in radians.roll
- Roll angle in radians.public void setAOA(double value)
value
- Angle of attack in radians.public void setSideslip(double value)
value
- Sideslip angle in radians.public void setRoll(double value)
value
- Roll angle in radians.public double getAOA()
public double getSideslip()
public double getRoll()
public void setWindAxesForces(double CL, double CD, double CY)
CL
- Wind axis lift force coefficient.CD
- Wind axis drag force coefficient.CY
- Wind axis side force coefficient.setAngles(double, double, double)
public void setWindAxesMoments(double CM, double Cn, double Cl)
CM
- Wind axis pitching moment coefficient.Cn
- Wind axis yawing moment coefficient.Cl
- Wind axis rolling moment coefficient.setAngles(double, double, double)
public double getCL()
setAngles(double, double, double)
public double getCD()
setAngles(double, double, double)
public double getCY()
setAngles(double, double, double)
public double getCM()
public double getCn()
public double getCl()
public void setStabilityAxesForces(double CLSA, double CDSA, double CYSA)
CLSA
- Stability axis lift force coefficient.CDSA
- Stability axis drag force coefficient.CYSA
- Stability axis side force coefficient.setAngles(double, double, double)
public void setStabilityAxesMoments(double CMSA, double CnSA, double ClSA)
CMSA
- Stability axis pitching moment coefficient.CnSA
- Stability axis yawing moment coefficient.ClSA
- Stability axis rolling moment coefficient.setAngles(double, double, double)
public double getCLSA()
setAngles(double, double, double)
public double getCDSA()
setAngles(double, double, double)
public double getCYSA()
setAngles(double, double, double)
public double getCMSA()
public double getCnSA()
public double getClSA()