* File : SenecaII.dat
* This is the datcom+ inputfile that models a
* Piper PA34-200T Seneca-II
* dimensions are picked from a Seneca II POH and D-GEJL
* 
* Author and (c): Torsten Dreyer (Torsten *at* t3r *dot* de)
*
* This program is free software; you can redistribute it and/or modify
* it under the terms of the GNU General Public License as published by
* the Free Software Foundation; either version 2 of the License, or
* (at your option) any later version.
*
* This program is distributed in the hope that it will be useful,
* but WITHOUT ANY WARRANTY; without even the implied warranty of
* MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the
* GNU General Public License for more details.
*
* You should have received a copy of the GNU General Public License
* along with this program; if not, write to the Free Software
* Foundation, Inc., 51 Franklin St, Fifth Floor, Boston, MA  02110-1301  USA
*
*
DIM FT
DAMP
DERIV RAD

 $FLTCON NMACH=2.0, 
         MACH(1)=0.245,0.269,
         NALT=2.0, 
         ALT(1)=0.0,10000.0,
         LOOP=1.0,
         NALPHA=20.0, 
         ALSCHD(1)= -8.0, -6.0, -4.0, -2.0,  0.0, 
                     2.0,  4.0,  6.0,  8.0, 10.0, 
                    12.0, 14.0, 15.0, 16.0, 16.2, 
                    16.4, 16.6, 16.8, 17.0, 17.2,
         STMACH=0.6,
         TSMACH=1.4,
         TR=1.0,
         WT=4500.0$

 $OPTINS ROUGFC=0.30E-3,
         SREF=208.7, CBARR=5.18, BLREF=38.906$

 $SYNTHS XCG=9.46, ZCG=0.0,
         XW=6.73, ZW=-1.08, ALIW=3.7,
         XH=24.9, ZH=0.623, ALIH=0.0, HINAX=25.9,
         XV=20.0, ZV=0.0,
         XVF=25.1,ZVF=0.0,
         VERTUP=.TRUE., SCALE=1.0$

* The shape of the body
 $BODY   NX=6.0,
         X(1) =0.0,  1.54, 6.56, 9.25, 15.7,  26.6,
         R(1) =0.0,  0.98, 2.03, 2.03,  2.03,  0.0,
         ZU(1)=3.61, 4.49, 5.31, 6.43,  5.64,  4.63,
         ZL(1)=3.61, 2.82, 2.46, 2.23,  2.07,  3.58,
         ITYPE=1.0, METHOD=1.0$

* The wing
 $WGPLNF CHRDTP=5.41, SSPNOP=14.8, SSPNE=17.5, SSPN=19.4,
         CHRDBP=5.42, CHRDR=7.36, SAVSI=25.0, CHSTAT=0.0,
         TWISTA=-3.0, DHDADI=7.0, TYPE=1.0$

NACA W 6 652-415

SAVE

* Flaps
 $SYMFLP FTYPE=2.0,
         NDELTA=4.0,
         DELTA(1)=0.0, 10.0, 25.0, 40.0,
         PHETE=0.0522, PHETEP=0.0391,
         CHRDFI=1.20, CHRDFO=1.20,
         SPANFI=2.00, SPANFO=12.4,
         CPRMEI(1)=6.6, 6.6, 6.7, 6.7,
         CPRMEO(1)=5.3, 5.3, 5.4, 5.4,
         NTYPE=1.0$

CASEID PA34-200T Seneca-II Flaps
NEXT CASE

* Ailerons
 $ASYFLP STYPE=4.0,
         NDELTA=9.0,
         DELTAL(1)=-28.0, -20.0, -10.0, -5.0, 0.0,  5.0,  10.0,  20.0,  28.0,
         DELTAR(1)= 28.0,  20.0,  10.0,  5.0, 0.0, -5.0, -10.0, -20.0, -28.0,
         SPANFI=12.4, SPANFO=18.8,
         PHETE=0.05228, CHRDFI=0.886, CHRDFO=0.886$

CASEID AILERONS: Piper PA34-200T Seneca-II Aircraft                                       
SAVE
NEXT CASE

TRIM

* Stabilizer
 $HTPLNF CHRDTP=2.89, SSPNE=6.16, SSPN=6.76, CHRDR=2.89,
         SAVSI=0.0, CHSTAT=0.0, TWISTA=0.0, DHDADI=0.0,
         TYPE=1.0$
NACA H 4 0011

#CASEID HSTAB: Piper PA34-200T Seneca-II Aircraft
#SAVE
#NEXT CASE

* All moveable horziontal tail
# $ASYFLP STYPE=5.0, NDELTA=9.0,
#         DELTAL(1)=-29.0, -20.0, -10.0, -5.0, 0.0,  5.0,  10.0,  20.0,  29.0,
#         DELTAR(1)=-29.0, -20.0, -10.0, -5.0, 0.0,  5.0,  10.0,  20.0,  29.0,
#         PHETE=0.001259$


* Vertical tail
 $VTPLNF CHRDTP=2.62, SSPNE=4.92, SSPN=6.23, CHRDR=6.56,
         SAVSI=39.8, CHSTAT=0.0, TYPE=1.0$

NACA V 4 0009

* Vertical fin
 $VFPLNF CHRDTP=0.0, SSPNE=0.75, SSPN=2.39, CHRDR=5.31,
         SAVSI=66.5, CHSTAT=0.0, TYPE=1.0$

NACA F 4 0009

* Groundeffect
* $GRNDEF NGH=6.0,
*         GRDHT=1.0, 2.0, 5.0, 10.0, 20.0, 50.0$

* Prop power
* $PROPWR NENGSP=2.0,
*         AIETLP=3.7,
*         THSTCP=0.0,
*         PHALOC=0.0,
*         PHVLOC=0.0,
*         PRPRAD=0.0,
*         ENGFCT=
         

CASEID TOTAL: PA34-200T Seneca-II Aircraft