pymead.analysis.calc_aero_data.MSESSettings#

class MSESSettings(xtrs: Dict[str, List[float]], Re: float = 10000000.0, Ma: float = 0.7, alfa_Cl_mode: int = 0, momentum_isentropic_mode: int = 3, boundary_condition_mode: int = 2, alfa: float = 0.0, Cl: float = 0.0, visc: bool = True, N: float = 9.0, M_crit: float = 0.95, aritifical_dissipation: float = 1.05, timeout: float = 15.0, iterations: int = 100, verbose: bool = True, actuator_disk_side: List[int] | None = None, actuator_disk_xc_location: List[float] | None = None, actuator_disk_total_pressure_ratio: List[float] | None = None, actuator_disk_thermal_efficiency: List[float] | None = None)[source]#

Bases: object

__init__(xtrs: Dict[str, List[float]], Re: float = 10000000.0, Ma: float = 0.7, alfa_Cl_mode: int = 0, momentum_isentropic_mode: int = 3, boundary_condition_mode: int = 2, alfa: float = 0.0, Cl: float = 0.0, visc: bool = True, N: float = 9.0, M_crit: float = 0.95, aritifical_dissipation: float = 1.05, timeout: float = 15.0, iterations: int = 100, verbose: bool = True, actuator_disk_side: List[int] | None = None, actuator_disk_xc_location: List[float] | None = None, actuator_disk_total_pressure_ratio: List[float] | None = None, actuator_disk_thermal_efficiency: List[float] | None = None)[source]#

Defines a reasonable set of MSES flow parameters. Note that at most one actuator disk can be used except if MSES 3.13b is installed.

Parameters:

  • xtrs (Dict[str, List[float]]) – \(x/c\)-location of the transition point for each airfoil in the multi-element airfoil object. The keys represent the name of each airfoil as it appears in the MEA (for example, "Airfoil-1", "Airfoil-2", etc.). The values are two-element lists with the transition location for the upper and lower surfaces. Use [1.0, 1.0] for free transition on both surfaces.

  • Re (float) – Reynolds number for the analysis. Ignored if visc==False. Default: 1.0e7

  • Ma (float) – Mach number for the analysis. Default: 0.7

  • alfa_Cl_mode (int) – To target an angle of attack, use mode==0. To target a lift coefficient, use mode==1. Default: 0

  • momentum_isentropic_mode (int) – Which set of momentum/isentropic equations to use for the MSES solution. If 1, use the S-momentum equation. If 2, use the isentropic condition everywhere. If 3, use the S-momentum equation everywhere, except use the isentropic condition at the leading edges. If 4, use the isentropic condition everywhere, except use the S-momentum equation where dissipation is active. Default: 3

  • boundary_condition_mode (int) – Which set of boundary conditions to use for the MSES solution. If 1, use the solid-wall airfoil far-field boundary condition. If 2, use the vortex+source+doublet airfoil far-field boundary condition. If 3, use the freestream pressure airfoil far-field boundary condition. If 4, use the supersonic wave freestream boundary condition. If 5, use the supersonic solid wall boundary condition. Default: 2

  • alfa (float) – Angle of attack in degrees. Ignored unless mode==0. Default: 0.0

  • Cl (float) – Lift coefficient. Ignored unless mode==1. Default: 0.0

  • visc (bool) – Whether to use a boundary layer model in the analysis. Default: True

  • N (float) – Envelope method exponent, 9.0 for an average wind tunnel. See the “Transition Criterion” section of the XFOIL user guide for more details and additional flow conditions. Default: 9.0

  • M_crit (float) – Critical Mach number. Use values below 1.0 for cases with stronger shocks. Default: 0.95

  • aritifical_dissipation (float) – Artificial dissipation constant. Use values above 1.0 for cases with strong shocks. Default: 1.05

  • timeout (float) – Maximum time in seconds allotted to MSES before premature termination occurs. Default: 15.0

  • iterations (int) – Maximum iterations allowed. Default: 100

  • verbose (bool) – Whether to print verbose output. Default: True

  • actuator_disk_side (List[int] or None) – Which airfoil side each actuator disk emanates from. The upper surface of the uppermost airfoil is side 1, the lower surface of the uppermost airfoil is side 2, the upper surface of the airfoil immediately below the uppermost airfoil is side 3, etc. Default: None

  • actuator_disk_xc_location (List[float] or None) – The \(x/c\)-location of each actuator disk on the airfoil sides given by actuator_disk_side. Default: None

  • actuator_disk_total_pressure_ratio (List[float] or None) – Total pressure ratio across each actuator disk. Default: None

  • actuator_disk_thermal_efficiency (List[float] or None) – Thermal efficiency of each actuator disk. A reasonable value for a modern fan is 0.95. Default: None

Methods

get_dict_rep()

Gets a Python dictionary representation of the MSES flow parameters.

Attributes

boundary_condition_mode_mapping

momentum_isentropic_mode_mapping

get_dict_rep() → dict[source]#

Gets a Python dictionary representation of the MSES flow parameters. Used in run_mses.

Returns:

The MSES flow parameters in dictionary form

Return type:

dict