AIM Inputs

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

• Proj_Name = "cbaero_CAPS"
  This corresponds to the project "root" name.
• Mach = 0.0 (default) or [0.0, ... , 0.0]
  Mach number (can be a single or array of values).
• Dynamic_Pressure = 0.0 (default) or [0.0, ... , 0.0]
  Dynamic pressure [bar] value (can be a single or array of values).
• Alpha = 0.0 (default) or [0.0, ... , 0.0]
  Angle of attack [degree] (can be a single or array of values).
• Beta = 0.0 (default) or [0.0, ... , 0.0]
  Sideslip angle (can be a single or array of values).
• 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).
• 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).
• Moment_Center = [0.0, 0.0, 0.0] (NULL)
  Array values correspond to the x, y, and z center of gravity (CG) locations [meter]. Alternatively, the geometry (body) attributes (see Attribution) "capsReferenceX", "capsReferenceY", and "capsReferenceZ" may be used to specify the center of gravity, respectively (note: values set through the AIM input will supersede the attribution values).
• Flow_Type = "Inviscid"
  Type of flow to consider. Options (=corresponding integer code): FreeTransition(=0), Laminar(=1), Turbulent(=2), Inviscid(=3).
• Critical_Transition = 220.0
  Critical ratio of Re-theta (Reynolds based on momentum thickness) and Ma (Mach number) for transition.
• Planet = "EARTH"
  Planet type. Options include “MERCURY”, “VENUS”, “EARTH”, “MARS”, “JUPITER”, “SATURN”, “URANUS”, “NEPTUNE”, and “PLUTO”.
• Default_Body_Method = "ModifiedNewtonian"
  Default hypersonic base method. Options (=corresponding integer code): ModifiedNewtonian(=3), TangentCone(=21), TangentConeNormalShock(=22), TangentWedge(=31), TangentWedgeNormalShock(=32), FreeMolecular(=99).
• Default_Wing_Method = "ModifiedNewtonian"
  Default hypersonic aerodynamic wing method. Options (=corresponding integer code): ModifiedNewtonian(=3), TangentCone(=21), TangentConeNormalShock(=22), TangentWedge(=31), TangentWedgeNormalShock(=32), FreeMolecular(=99).
• Default_Low_Speed_Method = "FastPanel"
  Default low speed method. Options (=corresponding integer code): FastPanel(=1), LowAR(=2).
• Leading_Edge_Suction = 1.00
  Default low speed method integer tag. Range [-1.0, 1.0]
• Mangler_Setting = "2D"
  Default low speed method. Options (=corresponding integer code): "2D"(=1), "Axisymmetric"(=2), "Auto"(=3).
• Aero_Surface = NULL
  Defines the type of aero. surface by associating a "capsGroups" attribute name with a particular panel method - ("capsGroup Name", "Value"), where "Value" can either be "Body", "Base", "Wing", "Inlet", "Cowl", or "Nozzle". If a capsGroup panel method is not defined it will be assumed to be a "Body".
• Material_Group = NULL
  Defines the type of aero. surface by associating a "capsGroups" attributes with a particular material group - ("Material Name", "Value"), where "Value" must be a JSON String dictionary, see CBAero Material Group for additional details.
• Trajectory = NULL
  List of trajectory file names
• TPSin = NULL
  Defines the .tpsin input file for TPSSizer, see CBAero TPS for additional details.
• TPS_Group = NULL
  Defines the type of aero. surface by associating a "capsGroups" attributes with a particular TPS zone - ("TPS Name", "Value"), where "Value" must be a JSON String dictionary, see CBAero TPS for additional details.
• TPSSizer = NULL
  Path to TPSSizer executable, e.g. "tpssizerv36_linux". If not specified only CBTPS will be executed when TPS information is provided.
• FIAT = NULL
  Name of FIAT excutable argument used with TPSSizer
• NumParallelCase = 1
  Set CBAero -mp to define number of Mach, dynamic pressure, and angle of attack cases to solve simultaneously.
  May be used in conjunction with NumThreadPerCase.
• NumThreadPerCase = 1
  Set CBAero -omp to define number of threads to solve a each Mach, dynamic pressure, and angle of attack cases.
  May be used in conjunction with NumParallelCase.
• Mesh_Morph = False
  Project previous surface mesh onto new geometry.
• Surface_Mesh = NULL
  A Surface_Mesh link.