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                                        ****************************************************
                                        *    USAF STABILITY AND CONTROL  DIGITAL DATCOM    *
                                        *    PROGRAM REV. JAN 96   DIRECT INQUIRIES TO:    *
                                        *   WRIGHT LABORATORY  (WL/FIGC)  ATTN: W. BLAKE   *
                                        *         WRIGHT PATTERSON AFB, OHIO  45433        *
                                        *    PHONE (513) 255-6764,   FAX (513) 258-4054    *
                                        ****************************************************
1                         CONERR - INPUT ERROR CHECKING
0 ERROR CODES - N* DENOTES THE NUMBER OF OCCURENCES OF EACH ERROR
0 A - UNKNOWN VARIABLE NAME
0 B - MISSING EQUAL SIGN FOLLOWING VARIABLE NAME
0 C - NON-ARRAY VARIABLE HAS AN ARRAY ELEMENT DESIGNATION - (N)
0 D - NON-ARRAY VARIABLE HAS MULTIPLE VALUES ASSIGNED
0 E - ASSIGNED VALUES EXCEED ARRAY DIMENSION
0 F - SYNTAX ERROR

0******************************  INPUT DATA CARDS  ******************************

  $FLTCON                                                                        
    NMACH=1.0,                                                                   
    MACH(1)=0.2,                                                                 
    NALPHA=18.0,                                                                 
    ALSCHD(1)=                                                                   
    -80.0,-60.0,-45.0,-30.0,-15.0,-10.0,-5.0,-2.0,                               
    0.0,                                                                         
    2.0,5.0,10.0,15.0,30.0,45.0,60.0,75.0,90.0,                                  
    NALT=1.0,                                                                    
    ALT(1)=5000.0,                                                               
    WT=12000.0,                                                                  
    LOOP=1.$                                                                     
  $SYNTHS                                                                        
    XCG=14.63,                                                                   
    ZCG=0.0,                                                                     
    XW=9.87,ZW=-1.04,                                                            
    ALIW=1.0,                                                                    
    XH=26.4,ZH=1.71,                                                             
    ALIH=0.0,                                                                    
    XV=20.93,ZV=0.0$                                                             
  $BODY NX=12.0,                                                                 
    X(1)=0.00,0.95,2.82,4.36,7.28,11.88,16.37,21.26,24.61,27.53,31.79,32.97,     
    S(1)=0.32,1.30,5.22,9.25,13.60,16.86,17.68,14.65,11.46,7.86,3.42,0.62$       
  $WGPLNF                                                                        
    CHRDTP=4.07,SSPNE=11.61,SSPN=14.0,                                           
    CHRDR=9.97,SAVSI=40.0,SAVSO=27.0,CHSTAT=0.25,                                
    TWISTA=2.0,DHDADI=1.30,TYPE=1.0$                                             
  $HTPLNF                                                                        
    CHRDTP=2.39,SSPNE=4.59,SSPN=6.07,CHRDR=3.48,SAVSI=33.0,                      
    CHSTAT=0.25,TYPE=1.0$                                                        
  $VTPLNF                                                                        
    CHRDTP=1.96,SSPNE=5.54,SSPN=8.0,CHRDR=10.43,SAVSI=42.0,                      
    CHSTAT=0.25,TYPE=1.0$                                                        
 NACA-W-6-65A112                                                                 
 NACA-H-6-65A010                                                                 
 NACA-V-6-65A010                                                                 
 DIM FT                                                                          
 DERIV DEG                                                                       
 DAMP                                                                            
 PART                                                                            
 PLOT                                                                            
 CASEID TOTAL: FIAT G91R4                                                        
1          THE FOLLOWING IS A LIST OF ALL INPUT CARDS FOR THIS CASE.
0
  $FLTCON                                                                        
    NMACH=1.0,                                                                   
    MACH(1)=0.2,                                                                 
    NALPHA=18.0,                                                                 
    ALSCHD(1)=                                                                   
    -80.0,-60.0,-45.0,-30.0,-15.0,-10.0,-5.0,-2.0,                               
    0.0,                                                                         
    2.0,5.0,10.0,15.0,30.0,45.0,60.0,75.0,90.0,                                  
    NALT=1.0,                                                                    
    ALT(1)=5000.0,                                                               
    WT=12000.0,                                                                  
    LOOP=1.$                                                                     
  $SYNTHS                                                                        
    XCG=14.63,                                                                   
    ZCG=0.0,                                                                     
    XW=9.87,ZW=-1.04,                                                            
    ALIW=1.0,                                                                    
    XH=26.4,ZH=1.71,                                                             
    ALIH=0.0,                                                                    
    XV=20.93,ZV=0.0$                                                             
  $BODY NX=12.0,                                                                 
    X(1)=0.00,0.95,2.82,4.36,7.28,11.88,16.37,21.26,24.61,27.53,31.79,32.97,     
    S(1)=0.32,1.30,5.22,9.25,13.60,16.86,17.68,14.65,11.46,7.86,3.42,0.62$       
  $WGPLNF                                                                        
    CHRDTP=4.07,SSPNE=11.61,SSPN=14.0,                                           
    CHRDR=9.97,SAVSI=40.0,SAVSO=27.0,CHSTAT=0.25,                                
    TWISTA=2.0,DHDADI=1.30,TYPE=1.0$                                             
  $HTPLNF                                                                        
    CHRDTP=2.39,SSPNE=4.59,SSPN=6.07,CHRDR=3.48,SAVSI=33.0,                      
    CHSTAT=0.25,TYPE=1.0$                                                        
  $VTPLNF                                                                        
    CHRDTP=1.96,SSPNE=5.54,SSPN=8.0,CHRDR=10.43,SAVSI=42.0,                      
    CHSTAT=0.25,TYPE=1.0$                                                        
 NACA-W-6-65A112                                                                 
 NACA-H-6-65A010                                                                 
 NACA-V-6-65A010                                                                 
 DIM FT                                                                          
 DERIV DEG                                                                       
 DAMP                                                                            
 PART                                                                            
 PLOT                                                                            
 CASEID TOTAL: FIAT G91R4                                                        
0 INPUT DIMENSIONS ARE IN FT, SCALE FACTOR IS 1.0000

1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM   
                                                        WING SECTION DEFINITION
                                                               NACA 65A112
     UPPER ABSCISSA     UPPER ORDINATE     LOWER ABSCISSA     LOWER ORDINATE      X-FRACTION CHORD    MEAN LINE    THICKNESS
          .00000             .00000            .00000            .00000               .00000            .00000        .00000
          .00076             .00444            .00124           -.00431               .00100            .00006        .00876
          .00170             .00626            .00230           -.00603               .00200            .00011        .01231
          .00265             .00765            .00335           -.00733               .00300            .00016        .01499
          .00362             .00882            .00438           -.00840               .00400            .00021        .01723
          .00460             .00984            .00540           -.00934               .00500            .00025        .01919
          .00557             .01076            .00643           -.01017               .00600            .00029        .02095
          .00656             .01160            .00744           -.01093               .00700            .00033        .02255
          .00754             .01238            .00846           -.01164               .00800            .00037        .02403
          .00852             .01311            .00948           -.01229               .00900            .00041        .02542
          .00951             .01380            .01049           -.01290               .01000            .00045        .02672
          .01943             .01925            .02057           -.01769               .02000            .00078        .03697
          .02938             .02333            .03062           -.02119               .03000            .00107        .04453
          .03936             .02669            .04064           -.02402               .04000            .00134        .05073
          .04934             .02960            .05066           -.02644               .05000            .00158        .05605
          .05933             .03218            .06067           -.02857               .06000            .00181        .06077
          .06933             .03452            .07067           -.03048               .07000            .00202        .06502
          .07933             .03667            .08067           -.03223               .08000            .00222        .06891
          .08933             .03865            .09067           -.03384               .09000            .00241        .07251
          .09934             .04051            .10066           -.03533               .10000            .00259        .07585
          .10934             .04225            .11066           -.03673               .11000            .00276        .07899
          .11935             .04388            .12065           -.03804               .12000            .00292        .08194
          .12936             .04543            .13064           -.03928               .13000            .00307        .08472
          .13937             .04690            .14063           -.04045               .14000            .00322        .08736
          .14938             .04829            .15062           -.04156               .15000            .00336        .08986
          .15939             .04962            .16061           -.04262               .16000            .00350        .09224
          .16940             .05087            .17060           -.04362               .17000            .00363        .09450
          .17942             .05207            .18058           -.04457               .18000            .00375        .09665
          .18943             .05321            .19057           -.04548               .19000            .00387        .09870
          .19944             .05430            .20056           -.04633               .20000            .00398        .10064
          .20946             .05533            .21054           -.04715               .21000            .00409        .10249
          .21948             .05631            .22052           -.04792               .22000            .00419        .10424
          .22949             .05724            .23051           -.04865               .23000            .00429        .10590
          .23951             .05811            .24049           -.04934               .24000            .00439        .10746
          .24952             .05894            .25048           -.04999               .25000            .00447        .10894
          .25954             .05972            .26046           -.05060               .26000            .00456        .11033
          .26956             .06045            .27044           -.05117               .27000            .00464        .11162
          .27958             .06113            .28042           -.05169               .28000            .00472        .11283
          .28959             .06176            .29041           -.05218               .29000            .00479        .11395
          .29961             .06235            .30039           -.05262               .30000            .00486        .11497
          .34971             .06451            .35029           -.05420               .35000            .00515        .11871
          .39981             .06536            .40019           -.05464               .40000            .00536        .12000
          .44991             .06483            .45009           -.05388               .45000            .00548        .11871
          .50000             .06302            .50000           -.05199               .50000            .00552        .11501
          .55009             .06005            .54991           -.04910               .55000            .00548        .10915
          .60016             .05604            .59984           -.04533               .60000            .00536        .10137
          .65023             .05111            .64977           -.04081               .65000            .00515        .09192
          .70027             .04539            .69973           -.03567               .70000            .00486        .08106
          .75030             .03899            .74970           -.03004               .75000            .00447        .06903
          .80031             .03202            .79969           -.02405               .80000            .00398        .05607
          .82031             .02881            .81969           -.02165               .82000            .00375        .05069
          .84030             .02560            .83970           -.01925               .84000            .00350        .04521
          .86029             .02240            .85971           -.01684               .86000            .00322        .03966
          .88027             .01920            .87973           -.01444               .88000            .00292        .03405
          .90025             .01599            .89975           -.01204               .90000            .00259        .02839
          .92022             .01279            .91978           -.00963               .92000            .00222        .02270
          .94019             .00959            .93981           -.00723               .94000            .00181        .01701
          .96014             .00639            .95986           -.00482               .96000            .00134        .01131
          .98009             .00319            .97991           -.00241               .98000            .00078        .00564
         1.00000             .00000           1.00000            .00000              1.00000            .00000        .00000
1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM   
                                                        WING SECTION DEFINITION
0                                 IDEAL ANGLE OF ATTACK =    .00000 DEG.

                              ZERO LIFT ANGLE OF ATTACK =   -.77637 DEG.

                                 IDEAL LIFT COEFFICIENT =    .10000

                  ZERO LIFT PITCHING MOMENT COEFFICIENT =   -.02177

                             MACH ZERO LIFT-CURVE-SLOPE =    .09448 /DEG.

                                    LEADING EDGE RADIUS =    .00993 FRACTION CHORD

                              MAXIMUM AIRFOIL THICKNESS =    .12000 FRACTION CHORD

                                                DELTA-Y =   2.51162 PERCENT CHORD


0                         MACH=  .2000 LIFT-CURVE-SLOPE =    .09620 /DEG.      XAC =    .26619
1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM   
                                                   HORIZONTAL TAIL SECTION DEFINITION
                                                               NACA 65A010
     UPPER ABSCISSA     UPPER ORDINATE     LOWER ABSCISSA     LOWER ORDINATE      X-FRACTION CHORD    MEAN LINE    THICKNESS
          .00000             .00000            .00000            .00000               .00000            .00000        .00000
          .00100             .00365            .00100           -.00365               .00100            .00000        .00731
          .00200             .00513            .00200           -.00513               .00200            .00000        .01026
          .00300             .00625            .00300           -.00625               .00300            .00000        .01250
          .00400             .00718            .00400           -.00718               .00400            .00000        .01437
          .00500             .00800            .00500           -.00800               .00500            .00000        .01600
          .00600             .00873            .00600           -.00873               .00600            .00000        .01746
          .00700             .00940            .00700           -.00940               .00700            .00000        .01880
          .00800             .01002            .00800           -.01002               .00800            .00000        .02003
          .00900             .01059            .00900           -.01059               .00900            .00000        .02119
          .01000             .01114            .01000           -.01114               .01000            .00000        .02227
          .02000             .01541            .02000           -.01541               .02000            .00000        .03082
          .03000             .01856            .03000           -.01856               .03000            .00000        .03712
          .04000             .02114            .04000           -.02114               .04000            .00000        .04228
          .05000             .02336            .05000           -.02336               .05000            .00000        .04672
          .06000             .02532            .06000           -.02532               .06000            .00000        .05065
          .07000             .02710            .07000           -.02710               .07000            .00000        .05419
          .08000             .02872            .08000           -.02872               .08000            .00000        .05744
          .09000             .03022            .09000           -.03022               .09000            .00000        .06043
          .10000             .03161            .10000           -.03161               .10000            .00000        .06322
          .11000             .03292            .11000           -.03292               .11000            .00000        .06583
          .12000             .03414            .12000           -.03414               .12000            .00000        .06829
          .13000             .03531            .13000           -.03531               .13000            .00000        .07061
          .14000             .03640            .14000           -.03640               .14000            .00000        .07281
          .15000             .03745            .15000           -.03745               .15000            .00000        .07489
          .16000             .03844            .16000           -.03844               .16000            .00000        .07687
          .17000             .03938            .17000           -.03938               .17000            .00000        .07875
          .18000             .04027            .18000           -.04027               .18000            .00000        .08055
          .19000             .04112            .19000           -.04112               .19000            .00000        .08225
          .20000             .04193            .20000           -.04193               .20000            .00000        .08387
          .21000             .04270            .21000           -.04270               .21000            .00000        .08541
          .22000             .04343            .22000           -.04343               .22000            .00000        .08687
          .23000             .04412            .23000           -.04412               .23000            .00000        .08825
          .24000             .04478            .24000           -.04478               .24000            .00000        .08955
          .25000             .04539            .25000           -.04539               .25000            .00000        .09078
          .26000             .04597            .26000           -.04597               .26000            .00000        .09194
          .27000             .04651            .27000           -.04651               .27000            .00000        .09302
          .28000             .04701            .28000           -.04701               .28000            .00000        .09403
          .29000             .04748            .29000           -.04748               .29000            .00000        .09496
          .30000             .04791            .30000           -.04791               .30000            .00000        .09581
          .35000             .04946            .35000           -.04946               .35000            .00000        .09892
          .40000             .05000            .40000           -.05000               .40000            .00000        .10000
          .45000             .04946            .45000           -.04946               .45000            .00000        .09893
          .50000             .04792            .50000           -.04792               .50000            .00000        .09584
          .55000             .04548            .55000           -.04548               .55000            .00000        .09096
          .60000             .04224            .60000           -.04224               .60000            .00000        .08447
          .65000             .03830            .65000           -.03830               .65000            .00000        .07660
          .70000             .03377            .70000           -.03377               .70000            .00000        .06755
          .75000             .02876            .75000           -.02876               .75000            .00000        .05752
          .80000             .02336            .80000           -.02336               .80000            .00000        .04673
          .82000             .02103            .82000           -.02103               .82000            .00000        .04224
          .84000             .01869            .84000           -.01869               .84000            .00000        .03768
          .86000             .01635            .86000           -.01635               .86000            .00000        .03305
          .88000             .01402            .88000           -.01402               .88000            .00000        .02837
          .90000             .01168            .90000           -.01168               .90000            .00000        .02366
          .92000             .00935            .92000           -.00935               .92000            .00000        .01892
          .94000             .00701            .94000           -.00701               .94000            .00000        .01417
          .96000             .00467            .96000           -.00467               .96000            .00000        .00943
          .98000             .00234            .98000           -.00234               .98000            .00000        .00470
         1.00000             .00000           1.00000            .00000              1.00000            .00000        .00000
1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM   
                                                   HORIZONTAL TAIL SECTION DEFINITION
0                                 IDEAL ANGLE OF ATTACK =    .00000 DEG.

                              ZERO LIFT ANGLE OF ATTACK =    .00000 DEG.

                                 IDEAL LIFT COEFFICIENT =    .00000

                  ZERO LIFT PITCHING MOMENT COEFFICIENT =    .00000

                             MACH ZERO LIFT-CURVE-SLOPE =    .09629 /DEG.

                                    LEADING EDGE RADIUS =    .00690 FRACTION CHORD

                              MAXIMUM AIRFOIL THICKNESS =    .10000 FRACTION CHORD

                                                DELTA-Y =   2.09333 PERCENT CHORD


0                         MACH=  .2000 LIFT-CURVE-SLOPE =    .09807 /DEG.      XAC =    .26341
1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM   
                                                    VERTICAL TAIL SECTION DEFINITION
                                                               NACA 65A010
     UPPER ABSCISSA     UPPER ORDINATE     LOWER ABSCISSA     LOWER ORDINATE      X-FRACTION CHORD    MEAN LINE    THICKNESS
          .00000             .00000            .00000            .00000               .00000            .00000        .00000
          .00100             .00365            .00100           -.00365               .00100            .00000        .00731
          .00200             .00513            .00200           -.00513               .00200            .00000        .01026
          .00300             .00625            .00300           -.00625               .00300            .00000        .01250
          .00400             .00718            .00400           -.00718               .00400            .00000        .01437
          .00500             .00800            .00500           -.00800               .00500            .00000        .01600
          .00600             .00873            .00600           -.00873               .00600            .00000        .01746
          .00700             .00940            .00700           -.00940               .00700            .00000        .01880
          .00800             .01002            .00800           -.01002               .00800            .00000        .02003
          .00900             .01059            .00900           -.01059               .00900            .00000        .02119
          .01000             .01114            .01000           -.01114               .01000            .00000        .02227
          .02000             .01541            .02000           -.01541               .02000            .00000        .03082
          .03000             .01856            .03000           -.01856               .03000            .00000        .03712
          .04000             .02114            .04000           -.02114               .04000            .00000        .04228
          .05000             .02336            .05000           -.02336               .05000            .00000        .04672
          .06000             .02532            .06000           -.02532               .06000            .00000        .05065
          .07000             .02710            .07000           -.02710               .07000            .00000        .05419
          .08000             .02872            .08000           -.02872               .08000            .00000        .05744
          .09000             .03022            .09000           -.03022               .09000            .00000        .06043
          .10000             .03161            .10000           -.03161               .10000            .00000        .06322
          .11000             .03292            .11000           -.03292               .11000            .00000        .06583
          .12000             .03414            .12000           -.03414               .12000            .00000        .06829
          .13000             .03531            .13000           -.03531               .13000            .00000        .07061
          .14000             .03640            .14000           -.03640               .14000            .00000        .07281
          .15000             .03745            .15000           -.03745               .15000            .00000        .07489
          .16000             .03844            .16000           -.03844               .16000            .00000        .07687
          .17000             .03938            .17000           -.03938               .17000            .00000        .07875
          .18000             .04027            .18000           -.04027               .18000            .00000        .08055
          .19000             .04112            .19000           -.04112               .19000            .00000        .08225
          .20000             .04193            .20000           -.04193               .20000            .00000        .08387
          .21000             .04270            .21000           -.04270               .21000            .00000        .08541
          .22000             .04343            .22000           -.04343               .22000            .00000        .08687
          .23000             .04412            .23000           -.04412               .23000            .00000        .08825
          .24000             .04478            .24000           -.04478               .24000            .00000        .08955
          .25000             .04539            .25000           -.04539               .25000            .00000        .09078
          .26000             .04597            .26000           -.04597               .26000            .00000        .09194
          .27000             .04651            .27000           -.04651               .27000            .00000        .09302
          .28000             .04701            .28000           -.04701               .28000            .00000        .09403
          .29000             .04748            .29000           -.04748               .29000            .00000        .09496
          .30000             .04791            .30000           -.04791               .30000            .00000        .09581
          .35000             .04946            .35000           -.04946               .35000            .00000        .09892
          .40000             .05000            .40000           -.05000               .40000            .00000        .10000
          .45000             .04946            .45000           -.04946               .45000            .00000        .09893
          .50000             .04792            .50000           -.04792               .50000            .00000        .09584
          .55000             .04548            .55000           -.04548               .55000            .00000        .09096
          .60000             .04224            .60000           -.04224               .60000            .00000        .08447
          .65000             .03830            .65000           -.03830               .65000            .00000        .07660
          .70000             .03377            .70000           -.03377               .70000            .00000        .06755
          .75000             .02876            .75000           -.02876               .75000            .00000        .05752
          .80000             .02336            .80000           -.02336               .80000            .00000        .04673
          .82000             .02103            .82000           -.02103               .82000            .00000        .04224
          .84000             .01869            .84000           -.01869               .84000            .00000        .03768
          .86000             .01635            .86000           -.01635               .86000            .00000        .03305
          .88000             .01402            .88000           -.01402               .88000            .00000        .02837
          .90000             .01168            .90000           -.01168               .90000            .00000        .02366
          .92000             .00935            .92000           -.00935               .92000            .00000        .01892
          .94000             .00701            .94000           -.00701               .94000            .00000        .01417
          .96000             .00467            .96000           -.00467               .96000            .00000        .00943
          .98000             .00234            .98000           -.00234               .98000            .00000        .00470
         1.00000             .00000           1.00000            .00000              1.00000            .00000        .00000
1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM   
                                                    VERTICAL TAIL SECTION DEFINITION
0                                 IDEAL ANGLE OF ATTACK =    .00000 DEG.

                              ZERO LIFT ANGLE OF ATTACK =    .00000 DEG.

                                 IDEAL LIFT COEFFICIENT =    .00000

                  ZERO LIFT PITCHING MOMENT COEFFICIENT =    .00000

                             MACH ZERO LIFT-CURVE-SLOPE =    .09629 /DEG.

                                    LEADING EDGE RADIUS =    .00690 FRACTION CHORD

                              MAXIMUM AIRFOIL THICKNESS =    .10000 FRACTION CHORD

                                                DELTA-Y =   2.09333 PERCENT CHORD


0                         MACH=  .2000 LIFT-CURVE-SLOPE =    .09807 /DEG.      XAC =    .26341
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                         CHARACTERISTICS AT ANGLE OF ATTACK AND IN SIDESLIP
                                        WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
                                                         TOTAL: FIAT G91R4
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0  .200    5000.00     219.39   1.7609E+03     500.843     1.2301E+06           196.560      7.433    28.000    14.630      .000
0                                                               -------------------DERIVATIVE (PER DEGREE)-------------------
0 ALPHA     CD       CL       CM       CN       CA       XCP        CLA          CMA          CYB          CNB          CLB
0
     .0     .017     .120    -.0454    .120     .017    -.377    6.443E-02   -3.127E-02   -1.167E-02    2.805E-03   -1.477E-03
  -80.0     .102    -.091   59.6615   -.116    -.072   ******   -5.040E-02   -3.005E+00                             -3.298E-03
  -60.0     .126    -.834   10.8473   -.526    -.659   ******   -3.487E-02   -1.389E+00                             -3.628E-04
  -45.0     .178   -1.331    1.8442  -1.067    -.815   -1.728   -1.745E-02   -3.430E-01                              1.848E-03
  -30.0     .169   -1.357     .5573  -1.260    -.532    -.442    1.506E-02   -4.579E-02                              2.484E-03
  -15.0     .080    -.879     .4704   -.870    -.151    -.541    5.990E-02   -2.766E-02                              1.622E-03
  -10.0     .038    -.533     .2957   -.531    -.055    -.556    6.837E-02   -3.535E-02                              5.367E-04
   -5.0     .018    -.195     .1169   -.196     .001    -.596    6.471E-02   -3.406E-02                             -5.211E-04
   -2.0     .015    -.006     .0178   -.007     .015   -2.621    6.321E-02   -3.218E-02                             -1.094E-03
     .0     .017     .120    -.0454    .120     .017    -.377    6.444E-02   -3.137E-02                             -1.477E-03
    2.0     .021     .252    -.1077    .252     .012    -.427    6.653E-02   -3.112E-02                             -1.881E-03
    5.0     .033     .455    -.2010    .457    -.006    -.440    6.875E-02   -3.199E-02                             -2.522E-03
   10.0     .071     .806    -.3684    .806    -.070    -.457    6.430E-02   -3.201E-02                             -3.636E-03
   15.0     .119    1.098    -.5211   1.092    -.170    -.477    4.325E-02   -2.580E-02                             -4.475E-03
   30.0     .131    1.058    -.6951    .982    -.416    -.708   -1.477E-02    6.094E-03                             -2.667E-03
   45.0     .084     .655    -.3383    .523    -.404    -.647   -1.714E-02    1.543E-02                             -3.485E-05
   60.0     .094     .544    -.2323    .354    -.424    -.657   -1.156E-02    1.050E-02                              1.196E-03
   75.0     .102     .309    -.0233    .179    -.272    -.130   -1.985E-02    1.737E-02                              2.642E-03
0                                    ALPHA     Q/QINF    EPSLON  D(EPSLON)/D(ALPHA)
0
                                       .0      1.000      1.525         .612
                                    -80.0      1.000       .000         .019
                                    -60.0      1.000       .000         .000
                                    -45.0      1.000       .000        -.144
                                    -30.0      1.000     -4.312        -.227
                                    -15.0      1.000     -6.817         .338
                                    -10.0      1.000     -4.284         .540
                                     -5.0      1.000     -1.420         .579
                                     -2.0      1.000       .327         .593
                                       .0      1.000      1.525         .612
                                      2.0      1.000      2.777         .637
                                      5.0      1.000      4.736         .665
                                     10.0      1.000      8.164         .663
                                     15.0      1.000     11.361         .519
                                     30.0      1.000     13.727        -.270
                                     45.0      1.000      3.247        -.458
                                     60.0      1.000       .000        -.108
                                     75.0      1.000       .000         .000
1                               AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                                         DYNAMIC DERIVATIVES
                                        WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
                                                         TOTAL: FIAT G91R4
 
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0  .200    5000.00     219.39   1.7609E+03     500.843     1.2301E+06           196.560      7.433    28.000    14.630      .000
                                                    DYNAMIC DERIVATIVES (PER DEGREE)
0           -------PITCHING-------    -----ACCELERATION------    --------------ROLLING--------------    --------YAWING--------
0   ALPHA       CLQ          CMQ           CLAD         CMAD         CLP          CYP          CNP          CNR          CLR
0
      .00    1.321E-01   -1.399E-01     2.725E-02   -5.506E-02   -5.323E-03    3.843E-04   -2.182E-04   -3.713E-03    1.762E-03
   -80.00                               8.484E-04   -1.714E-03    1.006E-03   -8.080E-03    1.246E-04   -8.259E-05   -9.096E-04
   -60.00                                 NDM          NDM       -3.103E-04   -7.664E-03    4.071E-03   -5.444E-04   -2.509E-03
   -45.00                              -6.396E-03    1.292E-02   -1.353E-03   -1.414E-02    4.205E-03   -1.545E-03   -3.570E-03
   -30.00                              -1.011E-02    2.043E-02   -2.862E-03   -1.164E-02    3.855E-03   -2.506E-03   -3.208E-03
   -15.00                               1.505E-02   -3.040E-02   -5.526E-03   -6.507E-03    2.044E-03   -3.205E-03   -1.673E-03
   -10.00                               2.401E-02   -4.851E-02   -5.949E-03   -4.010E-03    1.191E-03   -3.343E-03   -4.123E-04
    -5.00                               2.575E-02   -5.203E-02   -5.384E-03   -1.787E-03    4.977E-04   -3.518E-03    7.405E-04
    -2.00                               2.636E-02   -5.326E-02   -5.205E-03   -4.917E-04    7.259E-05   -3.634E-03    1.353E-03
      .00                               2.725E-02   -5.506E-02   -5.323E-03    3.843E-04   -2.182E-04   -3.713E-03    1.762E-03
     2.00                               2.833E-02   -5.722E-02   -5.519E-03    1.277E-03   -5.105E-04   -3.795E-03    2.191E-03
     5.00                               2.960E-02   -5.980E-02   -5.743E-03    2.649E-03   -9.562E-04   -3.924E-03    2.863E-03
    10.00                               2.948E-02   -5.956E-02   -5.425E-03    5.135E-03   -1.835E-03   -4.159E-03    4.020E-03
    15.00                               2.309E-02   -4.666E-02   -3.633E-03    7.738E-03   -2.944E-03   -4.363E-03    4.885E-03
    30.00                              -1.203E-02    2.431E-02    8.137E-04    1.119E-02   -4.336E-03   -3.977E-03    3.152E-03
    45.00                              -2.036E-02    4.113E-02   -2.818E-04    1.029E-02   -3.819E-03   -3.068E-03    7.681E-04
    60.00                              -4.816E-03    9.729E-03   -2.033E-03    1.137E-02   -3.745E-03   -2.063E-03    1.842E-04
    75.00                                 NDM          NDM       -2.570E-03    1.170E-02   -2.786E-03   -1.042E-03   -2.991E-04
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
0*** VEHICLE WEIGHT =  12000.00 LB.
0*** LEVEL FLIGHT LIFT COEFFICIENT = 1.23823
1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                             CONFIGURATION AUXILIARY AND PARTIAL OUTPUT
                                        WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
                                                         TOTAL: FIAT G91R4
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0  .200    5000.00     219.39   1.7609E+03     500.843     1.2301E+06           196.560      7.433    28.000    14.630      .000


                                                       BASIC BODY PROPERTIES

            WETTED AREA      XCG     ZCG     BASE AREA     ZERO LIFT DRAG   BASE DRAG   FRICTION DRAG   PRESSURE DRAG
              .3767E+03    14.63     .00       5.3040         .7225E-02     .1735E-02     .5490E-02         NA  


                                         XCG RELATIVE TO THEORETICAL LEADING EDGE MAC=   -.93


                                                       BASIC PLANFORM PROPERTIES

                                    TAPER     ASPECT   QUARTER CHORD             QUARTER CHORD              ZERO LIFT    FRICTION
                         AREA       RATIO      RATIO       SWEEP        MAC        X(MAC)       Y(MAC)        DRAG     COEFFICIENT
0      WING
   TOTAL THEORITICAL
+                      .1966E+03     .408     .3989E+01    40.000     .743E+01     .174E+02     .602E+01                       
       TOTAL EXPOSED
+                      .1513E+03     .454     .3563E+01    40.000     .682E+01     .186E+02     .747E+01     .562E-02     .306E-02
0  HORIZONTAL TAIL
   TOTAL THEORITICAL
+                      .3563E+02     .687     .4136E+01    33.000     .297E+01     .291E+02     .285E+01                       
       TOTAL EXPOSED
+                      .2572E+02     .744     .3276E+01    33.000     .282E+01     .296E+02     .366E+01     .110E-02     .355E-02
0   VERTICAL TAIL
   TOTAL THEORITICAL
+                      .4956E+02     .188     .1291E+01    42.000     .716E+01     .263E+02     .309E+01                       
       TOTAL EXPOSED
+                      .2711E+02     .250     .1132E+01    42.000     .548E+01     .277E+02     .468E+01     .102E-02     .317E-02
0*** NA PRINTED WHEN METHOD NOT APPLICABLE
1                             AUTOMATED STABILITY AND CONTROL METHODS PER APRIL 1976 VERSION OF DATCOM
                                             CONFIGURATION AUXILIARY AND PARTIAL OUTPUT
                                        WING-BODY-VERTICAL TAIL-HORIZONTAL TAIL CONFIGURATION
                                                         TOTAL: FIAT G91R4
 -----------------------  FLIGHT CONDITIONS  ------------------------           --------------  REFERENCE DIMENSIONS  ------------
  MACH    ALTITUDE   VELOCITY    PRESSURE    TEMPERATURE     REYNOLDS             REF.      REFERENCE LENGTH   MOMENT REF. CENTER
 NUMBER                                                       NUMBER              AREA       LONG.     LAT.     HORIZ      VERT
             FT       FT/SEC     LB/FT**2       DEG R         1/FT               FT**2        FT        FT        FT        FT
0  .200    5000.00     219.39   1.7609E+03     500.843     1.2301E+06           196.560      7.433    28.000    14.630      .000
0          CLA-B(W)= 9.811E-03     CLA-W(B)= 4.586E-02     K-B(W)= 2.431E-01     K-W(B)= 1.137E+00     XAC/C-B(W)= 5.670E-01
0          CLA-B(H)= 2.536E-03     CLA-H(B)= 8.477E-03     K-B(H)= 3.601E-01     K-H(B)= 1.204E+00     XAC/C-B(H)= 2.046E-01
0                                      SIDEWASH, (1 + D(SIGMA)/D(BETA))QV/Q = 1.2881178E+00



                ALPHA         IV-B(W)          IV-W(H)          IV-B(H)          GAMMA/                  GAMMA/
                                                                              2*PI*ALPHA*V*R         (2*PI*ALPHA*V*R)T
                  .000        .0000E+00       -.9454E+00        .0000E+00        .0000E+00                .0000E+00
               -80.000       -.7622E-01       -.2405E+00       -.2422E+00        .4951E+00                .2122E+01
               -60.000       -.5807E-01       -.6130E+00       -.2497E+00        .4713E+00                .1607E+01
               -45.000       -.4381E-01       -.7473E+00       -.2517E+00        .4535E+00                .1271E+01
               -30.000       -.2894E-01       -.8328E+00       -.2423E+00        .4356E+00                .9676E+00
               -15.000        .0000E+00       -.8952E+00       -.1439E+00          NDM                    .5715E+00
               -10.000        .0000E+00       -.9129E+00        .0000E+00          NDM                      NDM 
                -5.000        .0000E+00       -.9296E+00        .0000E+00        .0000E+00                .0000E+00
                -2.000        .0000E+00       -.9392E+00        .0000E+00        .0000E+00                .0000E+00
                  .000        .0000E+00       -.9454E+00        .0000E+00        .0000E+00                .0000E+00
                 2.000        .0000E+00       -.9515E+00        .0000E+00        .0000E+00                .0000E+00
                 5.000        .0000E+00       -.9604E+00        .0000E+00        .0000E+00                .0000E+00
                10.000        .0000E+00       -.9747E+00        .0000E+00          NDM                      NDM 
                15.000        .0000E+00       -.9882E+00       -.1439E+00          NDM                    .5715E+00
                30.000       -.2894E-01       -.1023E+01       -.2423E+00        .4356E+00                .9676E+00
                45.000       -.4381E-01       -.1034E+01       -.2517E+00        .4535E+00                .1271E+01
                60.000       -.5807E-01       -.9495E+00       -.2497E+00        .4713E+00                .1607E+01
                75.000       -.7178E-01       -.5302E+00       -.2427E+00        .4891E+00                .1993E+01


                                                  DYNAMIC DERIVATIVE INCREMENTALS
          CLP(GAMMA=CL=0) =-2.8100E-01     CLP(GAMMA)/CLP (GAMMA=0) = 1.0034E+00      CNP/THETA =-3.5202E-04
                              CYP/GAMMA =-1.9190E-02                    CYP/CL (CL=0) = 5.1748E-01

                                             CLB/GAMMA        (CMO/THETA)W     (CMO/THETA)H
                                              -.1467E-03        -.3027E-02           NA  
0*** NDM PRINTED WHEN NO DATCOM METHODS EXIST
0*** NA PRINTED WHEN METHOD NOT APPLICABLE
1
1 END OF JOB.
