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YASim: Difference between revisions
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→Command Line: added advanced usage notes
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=== Command Line === | === Command Line === | ||
====Standard Usage==== | |||
By use of a standard command line, we can see what the YASim solver is calculating. First, open up a command line prompt, and enter in the location of YASim.exe, and then the location of the YASim xml file. For example, here's what you would type in for a standard Windows 32-bit installation, and viewing the [[Boeing 777-200ER]]'s YASim file. | By use of a standard command line, we can see what the YASim solver is calculating. First, open up a command line prompt, and enter in the location of YASim.exe, and then the location of the YASim xml file. For example, here's what you would type in for a standard Windows 32-bit installation, and viewing the [[Boeing 777-200ER]]'s YASim file. | ||
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* '''Approach Elevator:''' The approach elevator, from conditions at <[[YASim#approach|approach]]> in the xml file. | * '''Approach Elevator:''' The approach elevator, from conditions at <[[YASim#approach|approach]]> in the xml file. | ||
* '''CG:''' Center of gravity of the aircraft in coordinates. Unless it's supposed to be offset, it should always have a Y value of 0. | * '''CG:''' Center of gravity of the aircraft in coordinates. Unless it's supposed to be offset, it should always have a Y value of 0. | ||
====Advanced Usage==== | |||
The YASim standalone solver also has some command line flags that change it's behaviour. | |||
<code>Usage: yasim <ac.xml> [-g [-a alt] [-s kts]] </code> | |||
*'''-g :''' Instructs YASim to generate space separated tabular data instead of the usual solver output. This can be redirected to a file and used in various plotting programs to visualize the actual lift, drag, L/D curves. The columns of the output are: AoA, Lift, Drag, L/D. (aoa in degrees, lift and drag in G's) | |||
*'''-a alt:''' Run the solver at the given '''alt''' altitude in feet. | |||
*'''-s kts:''' Also run at the given airspeed '''kts''' in knots. | |||
Note that the above are for the aircraft taken as a whole, as solved by YASim, so they differ from the values of the wing airfoil. | |||
=== YASim design notes === | === YASim design notes === | ||