DIM M
DERIV RAD
PART
#DAMP

 $FLTCON WT=400., 
     LOOP=2.0, 
     NMACH=1.0, MACH(1)=0.125,
     NALT=1.0,  ALT(1)=1000.,
     NALPHA=20.0,
     ALSCHD(1)= -16.0, -8.0, -6.0, -4.0, -2.0, -1.0, 0.0, 1.0, 2.0,  4.0, 6.0,
         8.0, 10.0, 12.0, 14.0, 16.0, 18.0, 19.0, 20.0, 21.0,
     STMACH=0.7, TSMACH=1.4, TR=1.0$

 $OPTINS ROUGFC=0.25E-3, SREF=7.5$
# $OPTINS CBARR=2.5, BLREF=12.

 $SYNTHS XCG= 1.98, ZCG= 0.1,
         XW=1.733,ZW=-0.235, ALIW=2.0,
         XH= 3.8964,ZH= 0.1796, ALIH=0.,
         SCALE=1.0$
* Body

 $BODY NX=12.0,
     X(1) = 0.035, 0.169, 0.432, 0.953, 1.362, 1.639, 1.840, 2.114, 2.574,
         3.473, 4.199, 4.794,
  R(1) = 0.029, 0.136, 0.224, 0.250, 0.269, 0.287, 0.299, 0.292, 0.247,
         0.145, 0.059, 0.015,
  ZU(1)= 0.038, 0.153, 0.261, 0.436, 0.570, 0.634, 0.662, 0.662, 0.578,
         0.418, 0.295, 0.195,
  ZL(1)=-0.019, -0.142, -0.219, -0.264, -0.284, -0.302, -0.311, -0.307,
        -0.269, -0.187, -0.128, -0.074,
#  P(1) = 0.2065, 1.0121, 1.6579, 2.1439, 2.4845, 2.6976, 2.8047, 2.7736,
#         2.3939, 1.5967, 0.9662, 0.5331,
#  S(1) = 0.0030, 0.0716, 0.1922, 0.3129, 0.4100, 0.4804, 0.5194, 0.5057,
#         0.3732, 0.1564, 0.0445, 0.0073,
  P(1) = 0.1965, 0.9634, 1.5782, 2.0409, 2.3651, 2.5679, 2.6699, 2.6402,
         2.2788, 1.5199, 0.9198, 0.5075, 
  S(1) = 0.0028, 0.0682, 0.1830, 0.2979, 0.3902, 0.4573, 0.4944, 0.4814,
         0.3553, 0.1489, 0.0423, 0.0069, 

       BNOSE=2.0, BTAIL=1.0,
       BLN=.25,   BLA=1.0,
       ITYPE=3.0, METHOD=1.0$
 $WGPLNF CHRDTP=1.029, CHRDR=1.029,
         SSPN= 2.7432,SSPNE=2.460,
         SAVSI= 0.0,   CHSTAT=0.0,
         TWISTA=0.0, DHDADI=3.0,  TYPE=1.0$
NACA W 6 64-415

 $ASYFLP STYPE=4.0, NDELTA=9.0,
         DELTAL(1)=-32.0,-20.0,-10.0,-5.0,0.0,5.0,10.0,20.0,32.0,
         DELTAR(1)=32.0,20.0,10.0,5.0,0.0,-5.0,-10.0,-20.0,-32.0,
         SPANFI=1.676, SPANFO=2.74,
         PHETE=0.05228,
         CHRDFI=.189, CHRDFO=.189$

CASEID AILERONS: SubSonex
#DAMP
SAVE
#DUMP DYN
NEXT CASE

 $HTPLNF TYPE=1.0,    CHRDR=0.788,CHRDTP=0.357,
         SSPNE=0.90, SSPN=0.936, SAVSI=0.0,
         CHSTAT=1.0, TWISTA=0.0, DHDADI=37.0,
         SHB=0., SEXT=0., RLPH=6.66$ ! I Guessed at these numbers

NACA H 4 0009

***********************************
*    Elevator Deflection parameters
***********************************
*   FTYPE   Flap type
*              1.0  Plain flaps
*   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
*   CB      Average chord of the balance    (plain flaps only)
*   TC      Average thickness of the control at hinge line
*           (plain flaps only)

 $SYMFLP FTYPE=1.0,
         NDELTA=9.0, DELTA(1)=-20.0,-15.0,-10.0,-5.0,0.0,5.0,10.0,15.0,20.0,
         PHETE=0.0522, PHETEP=0.0523,
         CHRDFI=0.345,  CHRDFO=.269,
         SPANFI=0.18,   SPANFO=1.04,
         CB=0.84,      TC=0.1,         NTYPE=1.0$ 

CASEID ----- SubSonex Final ----- 
#DAMP
TRIM
SAVE
NEXT CASE