NACAAirfoil (Autonomous Unmanned Vehicle (AUV) Workbench Documentation)

java.lang.Object
- dynamics.models.uav.NACAAirfoil

Direct Known Subclasses:

UAVFuselage
```
public class NACAAirfoil
extends Object
```

Field Summary

Fields
Modifier and Type	Field and Description
`protected double`	`aoa` Angle of attack in degrees (works better in the equations) associated with the current velocity
`protected double`	`area` Planform area of the airfoil section
`double`	`cDrag` Coefficient of drag for the current velocity and control setting
`protected double`	`chord` Airfoil chord width
`double`	`cLift` Coefficient of lift for the current velocity and control setting
`double`	`cMoment` Coefficient of moment of inertia about the aerodynamic center for the current velocity and control setting
`protected double`	`controlSetting` Current flap or aeleron setting
`protected int`	`controlType` integer designation for the airfoil control type (fixed, stabilator, or flapped)
`Vector3D`	`dragVector` Current drag force vector being generated by the airfoil
`static int`	`FIXED` Enumeration for type of airfoil
`static int`	`FLAPPED`
`Vector3D`	`liftVector` Current lifting force vector being generated by the airfoil
`static int`	`N0006` Enumeration for NACA airfoils covered in ref a.
`static int`	`N0009`
`static int`	`N0010_34`
`static int`	`N0010_35`
`static int`	`N0012`
`static int`	`N0012_64`
`static int`	`N1408`
`static int`	`N1410`
`static int`	`N1412`
`static int`	`N23012`
`static int`	`N23015`
`static int`	`N23018`
`static int`	`N23021`
`static int`	`N23024`
`static int`	`N2408`
`static int`	`N2410`
`static int`	`N2412`
`static int`	`N2415`
`static int`	`N2418`
`static int`	`N2421`
`static int`	`N2424`
`static int`	`N4412`
`static int`	`N4415`
`static int`	`N4418`
`static int`	`N4421`
`static int`	`N4424`
`static int`	`N63_006`
`static int`	`N63_009`
`static int`	`N63_012`
`static int`	`N63_015`
`static int`	`N63_018`
`static int`	`N63_021`
`static int`	`N63_206`
`static int`	`N63_209`
`static int`	`N63_210`
`static int`	`N63_212`
`static int`	`N63_215`
`static int`	`N63_218`
`static int`	`N63_221`
`static int`	`n63_412`
`static int`	`N63_415`
`static int`	`N63_418`
`static int`	`N63_421`
`static int`	`N63_615`
`static int`	`N63_618`
`static int`	`N63A010`
`static int`	`N63A020`
`static int`	`N64_006`
`static int`	`N64_009`
`static int`	`N64_012`
`static int`	`N64_015`
`static int`	`N64_018`
`static int`	`N64_021`
`static int`	`N64_108`
`static int`	`N64_110`
`static int`	`N64_112`
`static int`	`N64_206`
`static int`	`N64_208`
`static int`	`N64_209`
`static int`	`N64_210`
`static int`	`N64_212`
`static int`	`N64_215`
`static int`	`N64_218`
`static int`	`N64_221`
`static int`	`N64_412`
`static int`	`N64_415`
`static int`	`N64_418`
`static int`	`N64_421`
`static int`	`N64_618`
`static int`	`N64A010`
`static int`	`N64A210`
`static int`	`N64A212`
`static int`	`N64A215`
`static int`	`N64A410`
`static int`	`N65_006`
`static int`	`N65_009`
`static int`	`N65_012`
`static int`	`N65_015`
`static int`	`N65_018`
`static int`	`N65_021`
`static int`	`N65_206`
`static int`	`N65_209`
`static int`	`N65_210`
`static int`	`N65_212`
`static int`	`N65_215`
`static int`	`N65_218`
`static int`	`N65_221`
`static int`	`N65_410`
`static int`	`N65_412`
`static int`	`N65_415`
`static int`	`N65_418`
`static int`	`N65_421`
`static int`	`N65_618`
`static int`	`N66_006`
`static int`	`N66_009`
`static int`	`N66_012`
`static int`	`N66_015`
`static int`	`N66_018`
`static int`	`N66_021`
`static int`	`N66_206`
`static int`	`N66_209`
`static int`	`N66_210`
`static int`	`N66_212`
`static int`	`N66_215`
`static int`	`N66_218`
`static int`	`N66_221`
`static int`	`N66_415`
`static int`	`N66_418`
`Vector3D`	`normal` Airfoil normal direction (unit vector in body fixed coordinates)
`protected Vector3D`	`position` Position of the airfoil center of lift in body coordinates of the vehicle to which it is attached
`protected double`	`span` Airfoil span width
`static int`	`STABILATOR`
`Vector3D`	`velocity` Current velocity of the airfoil in body coordinates

Constructor Summary

Constructors
Constructor and Description
`NACAAirfoil(String id, int designation, double chord, double span, Vector3D position, Vector3D normal, int controlType)` Creates a new NACAAirfoil object

Method Summary

All Methods Instance Methods Concrete Methods
Modifier and Type	Method and Description
`Vector3D`	`dragVector(double altitude)` Calculates the drag force applied to the airfoil given its current velocity and altitude NOTE: Since this method depends on cDrag, if the velocity changes, setCoefficients should be called prior to this method to ensure accuracy
`double`	`dynamicPressure(double altitude)` Computes the dynamic pressure of the airfoil given a velocity vector
`double`	`dynamicPressure(Vector3D velocity, double altitude)` Computes the dynamic pressure of the airfoil given a scalar velocity
`Vector3D`	`foilVelocity(Vector3D linearVelocity, Vector3D angularVelocity)` Computes the velocity of the center of lift given the rigid body's linear and angular velocities
`Vector3D`	`liftVector(double altitude)` Calculates the lifting force applied to the airfoil given its current velocity and altitude NOTE: Since this method depends on cLift, if the velocity changes, setCoefficients should be called prior to this method to ensure accuracy
`double`	`maxNonStallAOA()` Computes the maximum non-stall angle of attack for the current control setting
`double`	`minNonStallAOA()` Computes the minimum non-stall angle of attack for the current control setting
`double`	`reynoldsNumber(double velocity, double altitude)` Computes the Reynolds number of the airfoil given an altitude and scalar velocity
`double`	`reynoldsNumber(Vector3D velocity, double altitude)` Computes the Reynolds number of the airfoil given an altitude and vector velocity
`double`	`setAOA(Vector3D velocity)` Computes the angle of attack given the velocity of the airfoil The angle of attack is computed as the angle between the normal and the lift vector
`void`	`setCoefficients(Vector3D velocity)` Sets the airfoil's current lift, drag, and moment of inertia coefficients, and angle of attack
`void`	`setControl(double setting)` Sets the flap or stabilator orientation of the airfoil
`double`	`setDragCoefficient()` Computes the airfoil's current drag coefficient Since the C_Drag and C_Moment depend on C_Lift, if AOA (velocity) changes, setLiftCoefficient should be called prior to setDragCoefficient and setMomentCoefficient for correct results Control setting is not relevant here because it is already factored into C_Lift
`double`	`setLiftCoefficient()` Computes the airfoil's current lift coefficient Since the C_Drag and C_Moment depend on C_Lift, if AOA (velocity) changes, this method should be called prior to setDragCoefficient and setMomentCoefficient for correct results
`Vector3D`	`torqueVector()` Calculates the total moment about the rigid body center of gravity due to aerodynamic forces acting on this airfoil.
`Vector3D`	`unitDrag(Vector3D velocity)` Computes the unit vector direction of airfoil drag given the velocity Drag direction is directly opposite velocity
`Vector3D`	`unitLift(Vector3D velocity)` Computes the unit vector direction of airfoil lift given the velocity Lift direction is perpendicular to drag and in the plane formed by the drag and normal vectors computed as D x N x D

Methods inherited from class java.lang.Object
clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

- Field Detail
  - FIXED
```
public static final int FIXED
```
    Enumeration for type of airfoil
    
    See Also:
    
    Constant Field Values
  - STABILATOR
```
public static final int STABILATOR
```
    See Also:
    
    Constant Field Values
  - FLAPPED
```
public static final int FLAPPED
```
    See Also:
    
    Constant Field Values
  - controlType
```
protected int controlType
```
    integer designation for the airfoil control type (fixed, stabilator, or flapped)
  - chord
```
protected double chord
```
    Airfoil chord width
  - span
```
protected double span
```
    Airfoil span width
  - area
```
protected double area
```
    Planform area of the airfoil section
  - position
```
protected Vector3D position
```
    Position of the airfoil center of lift in body coordinates of the vehicle to which it is attached
  - normal
```
public Vector3D normal
```
    Airfoil normal direction (unit vector in body fixed coordinates)
  - aoa
```
protected double aoa
```
    Angle of attack in degrees (works better in the equations) associated with the current velocity
  - velocity
```
public Vector3D velocity
```
    Current velocity of the airfoil in body coordinates
  - cLift
```
public double cLift
```
    Coefficient of lift for the current velocity and control setting
  - cDrag
```
public double cDrag
```
    Coefficient of drag for the current velocity and control setting
  - cMoment
```
public double cMoment
```
    Coefficient of moment of inertia about the aerodynamic center for the current velocity and control setting
  - liftVector
```
public Vector3D liftVector
```
    Current lifting force vector being generated by the airfoil
  - dragVector
```
public Vector3D dragVector
```
    Current drag force vector being generated by the airfoil
  - controlSetting
```
protected double controlSetting
```
    Current flap or aeleron setting
  - N0006
```
public static final int N0006
```
    Enumeration for NACA airfoils covered in ref a. Not all implemented here !!!
    
    See Also:
    
    Constant Field Values
  - N0009
```
public static final int N0009
```
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    Constant Field Values
  - N0010_34
```
public static final int N0010_34
```
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  - N0010_35
```
public static final int N0010_35
```
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  - N0012
```
public static final int N0012
```
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  - N0012_64
```
public static final int N0012_64
```
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  - N1408
```
public static final int N1408
```
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  - N1410
```
public static final int N1410
```
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  - N1412
```
public static final int N1412
```
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  - N2408
```
public static final int N2408
```
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  - N2410
```
public static final int N2410
```
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  - N2412
```
public static final int N2412
```
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  - N2415
```
public static final int N2415
```
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  - N2418
```
public static final int N2418
```
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  - N2421
```
public static final int N2421
```
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  - N2424
```
public static final int N2424
```
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  - N4412
```
public static final int N4412
```
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  - N4415
```
public static final int N4415
```
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  - N4418
```
public static final int N4418
```
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  - N4421
```
public static final int N4421
```
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  - N4424
```
public static final int N4424
```
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  - N23012
```
public static final int N23012
```
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  - N23015
```
public static final int N23015
```
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  - N23018
```
public static final int N23018
```
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  - N23021
```
public static final int N23021
```
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  - N23024
```
public static final int N23024
```
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  - N63_006
```
public static final int N63_006
```
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  - N63_009
```
public static final int N63_009
```
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  - N63_206
```
public static final int N63_206
```
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  - N63_209
```
public static final int N63_209
```
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  - N63_210
```
public static final int N63_210
```
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  - N63_012
```
public static final int N63_012
```
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  - N63_212
```
public static final int N63_212
```
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  - n63_412
```
public static final int n63_412
```
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  - N63_015
```
public static final int N63_015
```
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  - N63_215
```
public static final int N63_215
```
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  - N63_415
```
public static final int N63_415
```
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  - N63_615
```
public static final int N63_615
```
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  - N63_018
```
public static final int N63_018
```
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  - N63_218
```
public static final int N63_218
```
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  - N63_418
```
public static final int N63_418
```
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  - N63_618
```
public static final int N63_618
```
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  - N63_021
```
public static final int N63_021
```
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  - N63_221
```
public static final int N63_221
```
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  - N63_421
```
public static final int N63_421
```
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  - N63A010
```
public static final int N63A010
```
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  - N63A020
```
public static final int N63A020
```
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  - N64_006
```
public static final int N64_006
```
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  - N64_009
```
public static final int N64_009
```
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  - N64_108
```
public static final int N64_108
```
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  - N64_110
```
public static final int N64_110
```
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  - N64_206
```
public static final int N64_206
```
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  - N64_208
```
public static final int N64_208
```
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  - N64_209
```
public static final int N64_209
```
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  - N64_210
```
public static final int N64_210
```
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  - N64_012
```
public static final int N64_012
```
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  - N64_112
```
public static final int N64_112
```
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  - N64_212
```
public static final int N64_212
```
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  - N64_412
```
public static final int N64_412
```
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  - N64_015
```
public static final int N64_015
```
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  - N64_215
```
public static final int N64_215
```
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  - N64_415
```
public static final int N64_415
```
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  - N64_018
```
public static final int N64_018
```
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  - N64_218
```
public static final int N64_218
```
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  - N64_418
```
public static final int N64_418
```
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  - N64_618
```
public static final int N64_618
```
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  - N64_021
```
public static final int N64_021
```
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  - N64_221
```
public static final int N64_221
```
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  - N64_421
```
public static final int N64_421
```
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  - N64A010
```
public static final int N64A010
```
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  - N64A210
```
public static final int N64A210
```
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  - N64A410
```
public static final int N64A410
```
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  - N64A212
```
public static final int N64A212
```
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  - N64A215
```
public static final int N64A215
```
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  - N65_006
```
public static final int N65_006
```
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  - N65_009
```
public static final int N65_009
```
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  - N65_206
```
public static final int N65_206
```
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  - N65_209
```
public static final int N65_209
```
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  - N65_210
```
public static final int N65_210
```
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  - N65_410
```
public static final int N65_410
```
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  - N65_012
```
public static final int N65_012
```
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  - N65_212
```
public static final int N65_212
```
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  - N65_412
```
public static final int N65_412
```
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  - N65_015
```
public static final int N65_015
```
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  - N65_215
```
public static final int N65_215
```
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  - N65_415
```
public static final int N65_415
```
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  - N65_018
```
public static final int N65_018
```
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  - N65_218
```
public static final int N65_218
```
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  - N65_418
```
public static final int N65_418
```
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  - N65_618
```
public static final int N65_618
```
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  - N65_021
```
public static final int N65_021
```
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  - N65_221
```
public static final int N65_221
```
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  - N65_421
```
public static final int N65_421
```
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  - N66_006
```
public static final int N66_006
```
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  - N66_009
```
public static final int N66_009
```
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  - N66_206
```
public static final int N66_206
```
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  - N66_209
```
public static final int N66_209
```
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  - N66_210
```
public static final int N66_210
```
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  - N66_012
```
public static final int N66_012
```
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  - N66_212
```
public static final int N66_212
```
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  - N66_015
```
public static final int N66_015
```
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  - N66_215
```
public static final int N66_215
```
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  - N66_415
```
public static final int N66_415
```
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  - N66_018
```
public static final int N66_018
```
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  - N66_218
```
public static final int N66_218
```
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  - N66_418
```
public static final int N66_418
```
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  - N66_021
```
public static final int N66_021
```
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  - N66_221
```
public static final int N66_221
```
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- Constructor Detail
  - NACAAirfoil
```
public NACAAirfoil(String id,
                   int designation,
                   double chord,
                   double span,
                   Vector3D position,
                   Vector3D normal,
                   int controlType)
```
    Creates a new NACAAirfoil object
    
    Parameters:
    
    id - a string identifying this airfoil (i.e. "port inboard")
    
    designation - the 4, 5 or 6-digit NACA designation being modeled
    
    chord - fore-aft length of the airfoil
    
    span - width of airfoil section
    
    position - of the wing center of lift in aircraft body coordinates
    
    normal - vector defining the up direction of the span
    
    controlType - can be FIXED, STABILATOR, or FLAPPED
- Method Detail
  - setControl
```
public void setControl(double setting)
```
    Sets the flap or stabilator orientation of the airfoil
    
    Parameters:
    
    setting - control setting
  - setCoefficients
```
public void setCoefficients(Vector3D velocity)
```
    Sets the airfoil's current lift, drag, and moment of inertia coefficients, and angle of attack
    
    Parameters:
    
    velocity - of the airfoil in body coordinates (u, v, w)
  - maxNonStallAOA
```
public double maxNonStallAOA()
```
    Computes the maximum non-stall angle of attack for the current control setting
  - minNonStallAOA
```
public double minNonStallAOA()
```
    Computes the minimum non-stall angle of attack for the current control setting
  - setLiftCoefficient
```
public double setLiftCoefficient()
```
    Computes the airfoil's current lift coefficient Since the C_Drag and C_Moment depend on C_Lift, if AOA (velocity) changes, this method should be called prior to setDragCoefficient and setMomentCoefficient for correct results
  - setDragCoefficient
```
public double setDragCoefficient()
```
    Computes the airfoil's current drag coefficient Since the C_Drag and C_Moment depend on C_Lift, if AOA (velocity) changes, setLiftCoefficient should be called prior to setDragCoefficient and setMomentCoefficient for correct results Control setting is not relevant here because it is already factored into C_Lift
  - foilVelocity
```
public Vector3D foilVelocity(Vector3D linearVelocity,
                             Vector3D angularVelocity)
```
    Computes the velocity of the center of lift given the rigid body's linear and angular velocities
    
    Parameters:
    
    linearVelocity - of the airfoil in body coordinates (u, v, w)
    
    angularVelocity - of the airfoil in body coordinates (p, q, r)
  - setAOA
```
public double setAOA(Vector3D velocity)
```
    Computes the angle of attack given the velocity of the airfoil The angle of attack is computed as the angle between the normal and the lift vector
    
    Parameters:
    
    velocity - velocity of the wing in body coordinates (u, v, w)
  - unitLift
```
public Vector3D unitLift(Vector3D velocity)
```
    Computes the unit vector direction of airfoil lift given the velocity Lift direction is perpendicular to drag and in the plane formed by the drag and normal vectors computed as D x N x D
    
    Parameters:
    
    velocity - of the airfoil in body coordinates (u, v, w)
    
    Returns:
    
    the vector direction of airfoil lift
  - unitDrag
```
public Vector3D unitDrag(Vector3D velocity)
```
    Computes the unit vector direction of airfoil drag given the velocity Drag direction is directly opposite velocity
    
    Parameters:
    
    velocity - of the airfoil in body coordinates (u, v, w)
  - liftVector
```
public Vector3D liftVector(double altitude)
```
    Calculates the lifting force applied to the airfoil given its current velocity and altitude NOTE: Since this method depends on cLift, if the velocity changes, setCoefficients should be called prior to this method to ensure accuracy
    
    Parameters:
    
    altitude - in meters above mean sea level
  - dragVector
```
public Vector3D dragVector(double altitude)
```
    Calculates the drag force applied to the airfoil given its current velocity and altitude NOTE: Since this method depends on cDrag, if the velocity changes, setCoefficients should be called prior to this method to ensure accuracy
    
    Parameters:
    
    altitude - in meters above mean sea level
  - torqueVector
```
public Vector3D torqueVector()
```
    Calculates the total moment about the rigid body center of gravity due to aerodynamic forces acting on this airfoil. NOTE: This method is dependent on liftVector, dragVector, and pitchingMoment, their values should be updated with the liftVector, dragVector, and pitchingMoment methods if the velocity has changed since their last update
  - dynamicPressure
```
public double dynamicPressure(double altitude)
```
    Computes the dynamic pressure of the airfoil given a velocity vector
    
    Parameters:
    
    altitude -
    
    Returns:
    
    the pressure given a velocity vector
  - dynamicPressure
```
public double dynamicPressure(Vector3D velocity,
                              double altitude)
```
    Computes the dynamic pressure of the airfoil given a scalar velocity
    
    Parameters:
    
    velocity - vector in body coordinates (u, v, w)
    
    altitude - in meters above mean sea level
  - reynoldsNumber
```
public double reynoldsNumber(double velocity,
                             double altitude)
```
    Computes the Reynolds number of the airfoil given an altitude and scalar velocity
    
    Parameters:
    
    velocity - meters per second
    
    altitude - in meters above mean sea level
  - reynoldsNumber
```
public double reynoldsNumber(Vector3D velocity,
                             double altitude)
```
    Computes the Reynolds number of the airfoil given an altitude and vector velocity
    
    Parameters:
    
    velocity - meters per second
    
    altitude - in meters above mean sea level

Class NACAAirfoil

Field Summary

Constructor Summary

Method Summary

Methods inherited from class java.lang.Object

Field Detail

FIXED

STABILATOR

FLAPPED

controlType

chord

span

area

position

normal

aoa

velocity

cLift

cDrag

cMoment

liftVector

dragVector

controlSetting

N0006

N0009

N0010_34

N0010_35

N0012

N0012_64

N1408

N1410

N1412

N2408

N2410

N2412

N2415

N2418

N2421

N2424

N4412

N4415

N4418

N4421

N4424

N23012

N23015

N23018

N23021

N23024

N63_006

N63_009

N63_206

N63_209

N63_210

N63_012

N63_212

n63_412

N63_015

N63_215

N63_415

N63_615

N63_018

N63_218

N63_418

N63_618

N63_021

N63_221

N63_421

N63A010

N63A020

N64_006

N64_009

N64_108

N64_110

N64_206

N64_208

N64_209

N64_210

N64_012

N64_112