AIM Inputs

The following list outlines the FlightStream inputs along with their default values available through the AIM interface.

• ProjName = "flightstream_CAPS"
  Name for files generated by fightstream AIM.
• FlightStream = "FlightStream"
  The name of the FlightStream executable. May include full path.
• Mach = NULL
  Mach number
• Alpha = NULL
  Angle of attack
• Beta = NULL
  Sideslip angle
• SweepRangeMach = NULL
  Use FligthStream Sweeper Toolbox to solver for a range of Mach numbers.
  SweepRangeMach is a vector of length 3 with [start, end, delta] Mach numbers.
  Only one of 'Mach', 'SweepRangeMach', or 'SweepRangeVelocity' must be specified.
• SweepRangeVelocity = NULL
  Use FligthStream Sweeper Toolbox to solver for a range of velocities.
  SweepRangeVelocity is a vector of length 3 with [start, end, delta] velocities.
  Only one of 'Mach', 'SweepRangeMach', or 'SweepRangeVelocity' must be specified.
• SweepRangeAlpha = NULL
  Use FligthStream Sweeper Toolbox to solver for a range of angles of attack.
  SweepRangeAlpha is a vector of length 3 with [start, end, delta] angles.
  Only one of 'Alpha' or 'SweepRangeAlpha' must be specified.
• SweepRangeBeta = NULL
  Use FligthStream Sweeper Toolbox to solver for a range of sideslip angles.
  SweepRangeBeta is a vector of length 3 with [start, end, delta] angles.
  Only one of 'Beta' or 'SweepRangeBeta' must be specified.
• SweepClear_Solution_After_Each_Run = False
  Re-initialize the solution between each analysis when using FligthStream Sweeper Toolbox.
• SweepReference_Velocity_Equals_Freestream = False
  Use the updated reference velocity when using FligthStream Sweeper Toolbox to sweep over Mach or Velocity.
• SweepExport_Surface_Data = NULL
  Export surface data while using FligthStream Sweeper Toolbox. Only one file format may be specified. Available options:
  
  • DAT
  • VTK
  • CSV
  • TXT
• Fluid_Properties = NULL
  Reference fluid properties. Altitude must be NULL. See FlightStream Fluid Properties.
• Altitude = NULL (default)
  Altitude used to compute Fluid Properties. The Fluid_Properties input must be NULL.
• Solver_Model = NULL (default)
  One of: "INCOMPRESSIBLE", "SUBSONIC_PRANDTL_GLAUERT", "TRANSONIC_FIELD_PANEL", "SUPERSONIC_LINEAR_DOUBLET", "TANGENT_CONE", "MODIFIED_NEWTONIAN"
• Wake_Termination = NULL (default)
  Wake termination x-location
• Stabilization = 1.0 (default)
  Stabilization value for Solver_Model "INCOMPRESSIBLE", "SUBSONIC_PRANDTL_GLAUERT", or "TRANSONIC_FIELD_PANEL"
• Wall_Collision_Avoidance = false (default)
  Enable wake Wall Collision Avoidance
• CCS_GeneralSurface = NULL (default)
  General surface information for CCS geometry. See Vortex Lattice Surface for additional details.
• CCS_LiftingSurface = NULL (default)
  Lifting surface information for CCS geometry. See Vortex Lattice Surface for additional details.
• CCS_Control = NULL (default)
  Control surface information for CCS geometry. See Vortex Lattice Control Surface for additional details.
• CCS_Revolution = NULL (default)
  Body of Revolution information for CCS geometry. Only one airfoil section and one body for the axis of revolution must be provided. See Vortex Lattice Surface for additional details.
• CCS_Annular = NULL (default)
  Nacelle and Annular body information for CCS geometry. See Vortex Lattice Surface for additional details.
• ReferenceChord = NULL
  This sets the reference chord for used in force and moment calculations. Alternatively, the geometry (body) attribute (see Attribution) "capsReferenceChord" maybe used to specify this variable (note: values set through the AIM input will supersede the attribution value).
• ReferenceSpan = NULL
  This sets the reference span for used in force and moment calculations. Alternatively, the geometry (body) attribute (see Attribution) "capsReferenceSpan" maybe used to specify this variable (note: values set through the AIM input will supersede the attribution value).
• ReferenceArea = NULL
  This sets the reference area for used in force and moment calculations. Alternatively, the geometry (body) attribute (see Attribution) "capsReferenceArea" maybe used to specify this variable (note: values set through the AIM input will supersede the attribution value).
• ReferenceX = NULL
  This sets the reference X for moment calculations. Alternatively, the geometry (body) attribute (see Attribution) "capsReferenceX" maybe used to specify this variable (note: values set through the AIM input will supersede the attribution value).
• ReferenceX = NULL
  This sets the reference Y for moment calculations. Alternatively, the geometry (body) attribute (see Attribution) "capsReferenceY" maybe used to specify this variable (note: values set through the AIM input will supersede the attribution value).
• ReferenceX = NULL
  This sets the reference Z for moment calculations. Alternatively, the geometry (body) attribute (see Attribution) "capsReferenceZ" maybe used to specify this variable (note: values set through the AIM input will supersede the attribution value).
• ReferenceVelocity = NULL
  This sets the reference velocity
• Pressure_Scale_Factor = 1.0
  Value to scale Pressure data when transferring data. Data is scaled based on Pressure = Pressure_Scale_Factor*Pressure.
• ConvergenceTol = 1.0e-5 (default)
  Solver convergence tolerance
• SolverIterations = NULL
  Maximum number of solver iterations
• SolverConvergence = NULL
  Solver convergence tolerance
• Export_Solver_Analysis = NULL
  List of file types to export. Available options:
  
  • Tecplot
  • VTK
  • CSV
  • BDF
  • Force_Distributions
• FlightScriptPre = NULL
  List of flight script commands injected in script.txt prior to INITIALIZE_SOLVER
• FlightScriptPost = NULL
  List of flight script commands to append at the end of script.txt
• Hidden = True
  Hide FlightStream GUI during execution on Windows
• Max_Parallel_Threads = NULL
  Maximum number of threads for FligthStream analysis
• SaveFSM = False
  Save a FlightStream .fsm file after analysis
• Mesh_Morph = False
  Project previous surface mesh onto new geometry.
• Surface_Mesh = NULL
  A Surface_Mesh link.