YASim: Difference between revisions

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YASim (view source)

Revision as of 21:38, 24 January 2018

246 bytes added ,  24 January 2018
Updated CLI output example
mNo edit summary
(Updated CLI output example)
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'''Example output'''
'''Example output'''
<pre>
<pre>
yasim dhc6.xml  
yasim CRJ700.xml  
==========================
==========================
= YASim solution results =
= YASim solution results =
==========================
==========================
       Iterations: 1050
Iterations       : 1024
Drag Coefficient: 22.274
Drag Coefficient : 17.707
      Lift Ratio: 73.247
Lift Ratio       : 145.841
      Cruise AoA: -3.52 deg
Cruise AoA       : -0.11 deg
  Tail Incidence: 5.19 deg
Tail Incidence   : 3.47 deg
Approach Elevator: -0.848
Approach Elevator : -0.792


               CG: x:0.439, y:0.000, z:0.012
CG               : x:-0.046, y:0.000, z:-1.222
        Wing MAC: (x:1.00, y:5.29), length:2.0
Wing MAC         : (x:0.79, y:4.99), length:3.4
  hard limit CG-x: 4.468 m
hard limit CG-x   : 14.232 m
  soft limit CG-x: 0.500 m
soft limit CG-x   : -0.058 m
            CG-x: 0.439 m
CG-x             : -0.046 m
    CG-x rel. MAC:  28%
CG-x rel. MAC     :  25%
  soft limit CG-x: 0.400 m
soft limit CG-x   : -0.228 m
  hard limit CG-x: -1.000 m
hard limit CG-x   : -0.986 m


        wing span: 19.58 m
wing lever        : -0.012 m
sweep lead. edge: 0.0 .. 0.0 deg
tail lever        : -13.997 m
        wing area: 35.95 m²
  wing load empty: 94.63 kg/m² (Empty 3402 kg)
  wing load MTOW: 157.71 kg/m² (MTOW  5670 kg)


        tail span: 6.460 m
max thrust        : 157.18 kN
        tail area: 8.820 m²
thrust/empty      : 0.81
thrust/mtow      : 0.49


      wing lever: 0.061 m
wing span        : 22.64 m
      tail lever: -7.559 m
sweep lead. edge  : 30.2 .. 30.6 deg
wing area        : 58.70 m^2
wing load empty  : 336.15 kg/m^2 (Empty 19731 kg)
wing load MTOW    : 562.18 kg/m^2 (MTOW  32999 kg)


      max thrust: 36.36 kN
tail span        : 8.533 m
    thrust/empty: 1.09
tail area        : 14.838 m^2
      thrust/mtow: 0.65
 
#wing sections: 2
Section 0 base point (0.450, 1.226, -2.034), chord 5.085, incidence at section root 5.0deg
Section 1 base point (-0.663, 4.754, -1.942), chord 3.204, incidence at section root 3.0deg


Inertia tensor [kg*m^2], origo at CG:
Inertia tensor [kg*m^2], origo at CG:


    47625,     -0,   15426
  195646,       0, 122265
      -0,   61844,     60
        0, 1757279,       0
    15426,     60,   91592
  122265,       0, 1904528
</pre>
</pre>


Jsb
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