*
*  Navion, from Datcom Plotting Report 19830012662_1983012662.pdf
*
*  Values added by Bill Galbraith, December 2007
*  Some corrections by Ron Jensen, May 2009



**********************  
*  Flight Conditions *
**********************

*   WT      Vehicle Weight
*   LOOP    Program Looping Control
*              1 = vary altitude and mach together, default)
*              2 = vary Mach, at fixed altitude
*              3 = vary altitude, at fixed Mach
*   NMACH   Number of Mach numbers or velocities to be run, max of 20
*           Note: This parameter, along with NALT, may affect the
*           proper setting of the LOOP control parameter. 
*   MACH    Array(20) Values of freestream Mach number   
*   VINF    Array(20) Values of freestream speed (unit: l/t)
*   NALPHA  Number of angles of attack to be run, max of 20
*   ALSCHD  Array(20) Values of angles of attack, in ascending order
*   RNNUB   Array(20) Reynolds number per unit length
*           Freestream Reynolds numbers. Each array element must 
*           correspond to the respective Mach number/freestream 
*           speed input, use LOOP=1.0
*   NALT    Number of atmospheric conditions to be run, max of 20
*           input as either altitude or pressure and temperature
*           Note: This parameter, along with NMACH, may affect the
*           proper setting of the LOOP control parameter. 
*   ALT     Array(20) Values of geometric altitude
*           Number of altitude and values. Note, Atmospheric conditions 
*           are input either as altitude or pressure and temperature. (MAX 20)
*   PINF    Array(20) Values of freestream Static Pressure
*   TINF    Array(20) Values of freestream Temperature
*   HYPERS  =.true.  Hypersonic analysis at all Mach numbers > 1.4
*   STMACH  Upper limit of Mach numbers for subsonic analysis
*           (0.6<STMACH<0.99), Default to 0.6 if not input.
*   TSMACH  Lower limit of Mach number for Supersonic analysis 
*           (1.01<=TSMACH<=1.4)  Default to 1.4
*   TR      Drag due to lift transition flag, for regression analysis
*           of wing-body configuration.
*           = 0.0 for no transition (default)
*           = 1.0 for transition strips or full scale flight
*   GAMMA   Flight path angle

 $FLTCON LOOP=2.0, TR=1.0,
    NMACH=1.0,MACH(1)=0.158,
    NALPHA=9.0,ALSCHD(1)=-2.0,0.0,1.0,
       2.0,4.0,8.0,12.0,16.0,20.0,RNNUB(1)=1.07E6,
    PINF(1)=1967.62,NALT=1.0,ALT(1)=2000.0,
    VINF=176.0,TINF(1)=511.57,GAMMA=0.0,WT=2750.0$


*************************  
*  Reference Parameters *   pg 29
*************************

*   SREF    Reference area value of theoretical wing area used by program
*           if not input
*   CBARR   Longitudinal reference length value of theoritcal wing
*           Mean Aerodynamic Chord used by program if not input
*   BLREF   Lateral reference length value of wing span used by program
*   ROUGFC  Surface roughness factor, equivalent sand roughness, default
*           to 0.16e-3 inches (Natural sheet metal)
*           0.02/0.08E-3 - Polished metal or wood
*           0.16E-3  - Natural sheet metal
*           0.25E-3  - Smooth matte paint, carefully applied
*           0.40E-3  - Standard camouflage paint, average application

 $OPTINS SREF=184.0,CBARR=5.7,BLREF=33.4$





******************************************
* Group II     Synthesis Parameters
******************************************
*
*   page 33
*
*   XCG     Longitudinal location of cg (moment ref. center)
*   ZCG     Vertical location of CG relative to reference plane
*   XW      Longitudinal location of theoretical wing apex (where
*           leading edge would intersect long axis)
*   ZW      Vertical location of theoretical wing apex relative to
*           reference plane
*   ALIW    Wing root chord incident angle measured from reference plane
*   XH      Longitudinal location of theoretical horizontal tail apex. 
*           If HINAX is input, XH and ZH are evaluated at zero incidence.
*   ZH      Vertical location of theoretical horizontal tail apex
*           relative to reference plane. If HINAX is input, XH and ZH
*           are evaluated at zero incidence.
*   ALIH    Horizontal tail root chord incidence angle measured from
*           reference plane
*   XV      Longitudinal location of theoretical vertical tail apex
*   XVF     Longitudinal location of theoretical ventral fin apex
*   ZV      Vertical location of theoretical vertical tail apex
*           This kinda makes sense only for twin tails that are canted 
*   ZVF     Vertical location of theoretical ventral fin apex
*           This kinda makes sense only for twin tails that are canted 
*   SCALE   Vehicle scale factor (multiplier to input dimensions)
*   VERTUP  Vertical panel above reference plane (default=true)
*   HINAX   Longitudinal location of horizontal tail hinge axis.
*           Required only for all-moveable horizontal tail trim option.

 $SYNTHS XCG=8.03,ZCG=-0.47,XW=5.80,ZW=-2.12,ALIW=0.0,XH=21.64,
    ZV=0.0,XVF=19.76,ZVF=1.25,
    ZH=0.78,ALIH=0.0,XV=23.21,VERTUP=.TRUE.$



**********************************  
*  Body Configuration Parameters *
**********************************

*  page 36
*  Here is an error message output by DIGDAT concerning body geometry:
*   IN NAMELIST BODY, ONLY THE FOLLOWING COMBINATIONS OF VARIABLES CAN BE USED
*   FOR A CIRCULAR BODY, SPECIFY X AND R OR X AND S
*   FOR AN ELLIPTICAL BODY, SPECIFY X AND R OR X AND S, AND THE VARIABLE ELLIP
*   FOR OTHER BODY SHAPES X, R, S, AND P MUST ALL BE SPECIFIED
*   NX      Number of longitudinal body stations at which data is
*           specified, max of 20
*   X       Array(20) Longitudinal distance measured from arbitray location
*   S       Array(20) Cross sectional area at station. See note above.
*   P       Array(20) Periphery at station Xi. See note above.
*   R       Array(20) Planform half width at station Xi. See note above.
*   ZU      Array(20) Z-coordinate at upper body surface at station Xi
*           (positive when above centerline)
*           [Only required for subsonic asymmetric bodies]
*   ZL      Array(20) Z-coordinate at lower body surface at station Xi
*           (negative when below centerline)
*           [Only required for subsonic asymmetric bodies]
*   BNOSE   Nosecone type  1.0 = conical (rounded), 2.0 = ogive (sharp point)
*           [Not required in subsonic speed regime]
*   BTAIL   Tailcone type  1.0 = conical, 2.0 = ogive, omit for lbt = 0
*           [Not required in subsonic speed regime]
*   BLN     Length of body nose
*           Not required in subsonic speed regime
*   BLA     Length of cylindrical afterbody segment, =0.0 for nose alone
*           or nose-tail configuration
*           Not required in subsonic speed regime
*   DS      Nose bluntness diameter, zero for sharp nosebodies
*           [Hypersonic speed regime only]
*   ITYPE   1.0 = straight wing, no area rule
*           2.0 = swept wing, no area rule (default)
*           3.0 = swept wing, area rule
*   METHOD  1.0 = Use existing methods (default)
*           2.0 = Use Jorgensen method

 $BODY NX=18.0,ITYPE=1.0,
    ZU(1)=1.019,1.372,1.490,1.764,2.038,2.078,2.509,2.979,3.136,3.215,
       3.136,2.900,2.470,1.686,1.450,1.215,0.862,0.548,
    ZL(1)=-1.019,-1.372,-1.490,-1.764,-2.038,-2.117,-2.156,-2.195,
       -2.195,-2.195,-2.195,-2.156,-2.117,-1.960,-1.568,-1.176,-0.862,
       -0.392,
    X(1)=0.0,0.314,0.666,2.352,4.077,5.449,6.115,6.939,7.644,8.311,
       9.840,11.055,12.505,14.191,17.327,20.503,23.639,27.755,
    S(1)=3.765,6.422,7.433,9.992,12.799,13.815,15.802,17.685,
       18.552,18.823,18.384,17.130,14.969,10.887,6.881,3.904,2.163,0.125,
    P(1)=6.913,8.999,9.668,11.207,12.683,13.176,14.114,15.019,15.399,
       15.533,15.543,14.765,13.749,11.702,9.299,7.039,5.618,2.292,
    R(1)=1.116,1.490,1.568,1.803,1.999,2.097,2.156,2.176,2.215,2.215,
       2.195,2.156,2.078,1.901,1.410,1.039,0.627.0.078$


NACA-W-6-643-618
NACA-H-6-631-012
NACA-V-6-631-012



**********************************
*         Wing planform variables   pg 37-38
**********************************

*   CHRDR   Chord root
*   CHRDBP  Chord at breakpoint. Not required for straight 
*           tapered planform.
*   CHRDTP  Tip chord
*   SSPN    Semi-span theoretical panel from theoretical root chord
*   SSPNE   Semi-span exposed panel, See diagram on pg 37.
*   SSPNOP  Semi-span outboard panel. Not required for straight 
*           tapered planform.
*   SAVSI   Inboard panel sweep angle
*   SAVSO   Outboard panel sweep angle
*   CHSTAT  Reference chord station for inboard and outboard panel 
*           sweep angles, fraction of chord
*   TWISTA  Twist angle, negative leading edge rotated down (from 
*           exposed root to tip)
*   SSPNDD  Semi-span of outboard panel with dihedral
*   DHDADI  Dihedral angle of inboard panel
*   DHDADO  Dihedral angle of outboard panel. If DHDADI=DHDADO only 
*           input DHDADI
*   TYPE    1.0 - Straight tapered planform
*           2.0 - Double delta planform (aspect ratio <= 3)
*           3.0 - Cranked planform (aspect ratio > 3)

 $WGPLNF CHRDTP=3.73,SSPNE=14.43,SSPN=16.70,CHRDR=7.29,SAVSI=1.0,
         CHSTAT=0.25,TWISTA=0.0,DHDADI=8.5,DHDADO=0.0,TYPE=1.0$




******************************************
*         Vertical Tail planform variables   pg 37-38
******************************************

*   CHRDTP  Tip chord
*   SSPNOP  Semi-span outboard panel
*   SSPNE   Semi-span exposed panel
*   SSPN    Semi-span theoretical panel from theoretical root chord
*   CHRDBP  Chord at breakpoint
*   CHRDR   Chord root
*   SAVSI   Inboard panel sweep angle
*   SAVSO   Outboard panel sweep angle
*   CHSTAT  Reference chord station for inboard and outboard panel 
*           sweep angles, fraction of chord
*   TYPE    1.0 - Straight tapered planform
*           2.0 - Double delta planform (aspect ratio <= 3)
*           3.0 - Cranked planform (aspect ratio > 3)
*   SVWB    Portion of exposed vertical panel area that lies between 
*           Mach lines emanating from leading and trailing edges of 
*           wing exposed root chord (array 20)
*           Only required for supersonic and hypersonic speed regimes.
*   SVB     Area of exposed vertical panel not influenced by wing or 
*           horizontal tail (array 20)
*           Only required for supersonic and hypersonic speed regimes.
*   SVHB    Portion of exposed vertical panel area that lies between Mach 
*           lines emanating from leading and and trailing edges of 
*           horizontal tail exposed root chord (array 20)
*           Only required for supersonic and hypersonic speed regimes.

 $VTPLNF CHRDTP=1.88,SSPNE=4.39,SSPN=5.02,CHRDR=4.47,SAVSI=13.5,
    CHSTAT=.25,TYPE=1.0$




*********************************************
*         Horizontal Tail planform variables   pg 37-38
*********************************************

*   CHRDTP  Tip chord
*   SSPNOP  Semi-span outboard panel. Not required for straight 
*           tapered planform.
*   SSPNE   Semi-span exposed panel
*   SSPN    Semi-span theoretical panel from theoretical root chord
*   CHRDBP  Chord at breakpoint
*   CHRDR   Chord root
*   SAVSI   Inboard panel sweep angle
*   CHSTAT  Reference chord station for inboard and outboard panel 
*           sweep angles, fraction of chord
*   TWISTA  Twist angle, negative leading edge rotated down (from 
*           exposed root to tip)
*   SSPNDD  Semi-span of outboard panel with dihedral
*   DHDADI  Dihedral angle of inboard panel
*   DHDADO  Dihedral angle of outboard panel. If DHDADI=DHDADO only 
*           input DHDADI
*   TYPE    1.0 - Straight tapered planform
*           2.0 - Double delta planform (aspect ratio <= 3)
*           3.0 - Cranked planform (aspect ratio > 3)
*   SHB     Portion of fuselage side area that lies between Mach lines 
*           originating from leading and trailing edges of horizontal 
*           tail exposed root chord (array 20).
*           Only required for supersonic and hypersonic speed regimes.
*   SEXT     Portion of extended fueslage side area that lies between 
*            Mach lines originating from leading and trailing edges of 
*            horizontal tail exposed root chord (array 20)
*           Only required for supersonic and hypersonic speed regimes.
*   RLPH    Longitudinal distance between CG and centroid of Sh(B) 
*           positive aft of CG
*           Only required for supersonic and hypersonic speed regimes.

 $HTPLNF CHRDTP=2.51,SSPNE=6.19,SSPN=6.59,CHRDR=5.02,SAVSI=6.0,
    CHSTAT=0.25,TWISTA=0.0,DHDADI=0.0,DHDADO=0.0,TYPE=1.0$




***********************************
*    Elevator Deflection parameters
***********************************
*   FTYPE   Flap type
*              1.0  Plain flaps
*              2.0  Single slotted flaps
*              3.0  Fowler flaps
*              4.0  Double slotted flaps
*              5.0  Split flaps
*              6.0  Leading edge flap
*              7.0  Leading edge slats
*              8.0  Krueger
*   NDELTA  Number of flap or slat deflection angles, max of 9
*   DELTA   Flap deflection angles measured streamwise
*           (NDELTA values in array)
*   PHETE   Tangent of airfoil trailine edge angle based on ordinates at
*           90 and 99 percent chord
*   PHETEP  Tangent of airfoil trailing edge angle based on ordinates at
*           95 and 99 percent chord
*   CHRDFI  Flap chord at inboard end of flap, measured parallel to
*           longitudinal axis
*   CHRDFO  Flap chord at outboard end of flap, measured parallel to
*           longitudinal axis
*   SPANFI  Span location of inboard end of flap, measured perpendicular
*           to vertical plane of symmetry
*   SPANFO  Span location of outboard end of flap, measured perpendicular
*           to vertical plane of symmetry
*   CPRMEI  Total wing chord at inboard end of flap (translating devices 
*           only) measured parallel to longitudinal axis
*           (NDELTA values in array)
*              Single-slotted, Fowler, Double-slotted, leading-edge
*              slats, Krueger flap, jet flap
*   CPRMEO  Total wing chord at outboard end of flap (translating devices
*           only) measured parallel to longitudinal axis
*           (NDELTA values in array)
*              Single-slotted, Fowler, Double-slotted, leading-edge
*              slats, Krueger flap, jet flap
*   CAPINS  (double-slotted flaps only) (NDELTA values in array)
*   CAPOUT  (double-slotted flaps only) (NDELTA values in array)
*   DOSDEF  (double-slotted flaps only) (NDELTA values in array)
*   DOBCIN  (double-slotted flaps only)
*   DOBCOT  (double-slotted flaps only)
*   SCLD    Increment in section lift coefficient due to
*           deflecting flap to angle DELTA[i]      (optional)
*           (NDELTA values in array)
*   SCMD    Increment in section pitching moment coefficient due to
*           deflecting flap to angle DELTA[i]      (optional)
*           (NDELTA values in array)
*   CB      Average chord of the balance    (plain flaps only)
*   TC      Average thickness of the control at hinge line
*           (plain flaps only)
*   NTYPE   Type of nose
*              1.0  Round nose flap
*              2.0  Elliptic nose flap
*              3.0  Sharp nose flap
*   JETFLP  Type of flap
*              1.0  Pure jet flap
*              2.0  IBF
*              3.0  EBF
*   CMU     Two-dimensional jet efflux coefficient
*   DELJET  Jet deflection angle
*           (NDELTA values in array)
*   EFFJET  EBF Effective jet deflection angle
*           (NDELTA values in array)

 $SYMFLP FTYPE=1.0,
    NDELTA=9.0,DELTA(1)=-40.,-30.,-20.,-10.,0.,10.,20.,30.,40.,
    SPANFI=.400,SPANFO=6.586,CHRDFI=1.882,CHRDFO=.706,NTYPE=1.0,
    CB=.357,TC=.220,PHETE=.003,PHETEP=.002$



TRIM
DAMP
PART
DERIV RAD
CASEID NAVlON WITH ELEVATORS AND NO FLAPS OR AILERON DEFLECTIONS