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

• Mach = NULL
  Mach number.
• Re = 0.0
  Reynolds number. Use 0.0 for an inviscid calculation.
• Alpha = NULL
  Angle of attack [degree].
• CL = NULL
  Prescribed coefficient of lift.
• Acrit = 9.0
  Critical amplification factor "n" for the e^n envelope transition model. 9.0 is the standard model.
• xTransition_Upper = NULL
  List of forced transition location on the upper surface of each blade element. Must be equal in length to the number of blade elements.
• xTransition_Lower = NULL
  List of forced transition location on the lower surface of each blade element.
  Must be equal in length to the number of blade elements.
• Mcrit = 0.98
  "critical" Mach number above which artifical dissipation is added.
  0.99 usually for weak shocks
  0.90 for exceptionally strong shocks
  
• MuCon = 1.0
  artificial dissipation coefficient (1.0 works well),
  (A negative value disables the 2nd-order dissipation.
  This is a “last-resort” option for difficult cases.)
• ISMOM = 4
  MSES ISMOM input to select the momentum equation. Valid inputs: [1-4]
  1 -> use S-momentum equation
  2 -> use isentropic condition
  3 -> use S-momentum equation, with isentropic condition only near leading edge
  4 -> use isentropic condition, with S-momentum equation only where dissipation is active
• IFFBC = 2
  MSES IFFBC input to select the Farfield BC. Valid inputs: [1-5]
• Coarse_Iteration = 200
  Maximum number of coarse mesh iterations (can help convergence).
• Fine_Iteration = 200
  Maximum number of fine mesh iterations.
• GridAlpha = 0.0
  Angle of attack used to generate the grid.
• Airfoil_Points = 201
  Number of airfoil grid points created with mset
• Inlet_Points = NULL
  Inlet points on leftmost airfoil streamline created with mset
  If NULL, set to ~Airfoil_Points/4
• Outlet_Points = NULL
  Outlet points on rightmost airfoil streamline created with mset
  If NULL, set to ~Airfoil_Points/4
• Upper_Stremlines = NULL
  Number of streamlines in top of domain created with mset
  If NULL, set to ~Airfoil_Points/8
• Upper_Stremlines = NULL
  Number of streamlines in bottom of domain created with mset
  If NULL, set to ~Airfoil_Points/8
• xGridRange = [-1.75, 2.75]
  x-min and x-max values for the grid domain size.
• xGridRange = [-2.5, 2.5]
  x-min and x-max values for the grid domain size.
• Design_Variable = NULL
  The design variable tuple is used to input design variable information for the model optimization, see cfdDesignVariable for additional details. Must be NULL of Cheby_Modes is not NULL.
• Cheby_Modes = NULL
  List of Chebyshev shape mode values for shape optimization (must be even length with max length 40). Must be NULL if Design_Variable is not NULL