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twine.json
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{
"title": "Panel Codes FSI twine",
"description": "Uses potential theory to solve 2D airfoils",
"configuration_values_schema": {
"type": "object",
"properties": {
"analysis_program": {
"title": "Analysis Program",
"description": "The underlying program that will be run to determine aerofoil section properties",
"type": "string",
"default": "xfoil",
"anyOf": [
{
"type": "string",
"enum": [
"xfoil"
],
"title": "X-Foil"
},
{
"type": "string",
"enum": [
"vgfoil"
],
"title": "VG-Foil"
},
{
"type": "string",
"enum": [
"viiflow"
],
"title": "ViiFlow"
},
{
"type": "string",
"enum": [
"rfoil"
],
"title": "RFoil"
}
]
},
"silent_mode": {
"description": "Supress panel solver terminal output stream",
"type": "boolean",
"default": true
},
"max_iterations":{
"description": "Maximum number of iterations",
"type": "integer",
"title": "Max Iterations",
"default": 20,
"minimum": 20,
"maximum": 10000
}
}
},
"input_manifest":{
"datasets": {
"aerofoil_shape_data":{
"purpose": "A dataset containing shape files in .dat or tab delimited open form, describing the aerofoil shape."
}
}
},
"input_values_schema": {
"title": "Input values schema",
"type": "object",
"properties": {
"airfoil_geometry": {
"title": "Airfoil geometry",
"description": "Airfoil geometry specified as ordered xy pairs. Provided either as .dat file or as two separate, ordered arrays",
"type": "object",
"properties": {
"xy_coordinates":{
"title": "XY coordinates",
"description": "Two arrays of XY coordinates describing the aerofoil geometry, in a counterclockwise order",
"type": "object",
"properties": {
"x_coordinates": {
"type": "array"
},
"y_coordinates": {
"type": "array"
}
}
},
"airfoil_geometry_filename": {
"title": "Airfoil geometry filename",
"description": "Filename from the Dataset containing geometry files ex. naca_0012.dat",
"type": "string"
},
"repanel": {
"title": "Repanel Airfoil",
"description":"Use XFOIL routines to re-panel the geometry?",
"type": "boolean",
"default": false
},
"repanel_configuration": {
"type": "object",
"properties": {
"nodes": {
"description": "Number of nodes used to re-panel the airfoil",
"type": "integer"
}
}
}
}
},
"alpha_range": {
"description": "The range of alpha values at which the solver will be run.",
"type": "array",
"title": "Alpha Range [min max n-sample-points]",
"default": [0, 10, 11],
"prefixItems": [
{
"type": "number",
"minimum": -30,
"maximum": 30
},
{
"type": "number",
"minimum": -30,
"maximum": 30
},
{
"type": "integer",
"minimum": 1,
"maximum": 1000
}
],
"additionalItems": false
},
"inflow_speed": {
"title": "U",
"description": "Inflow speed U in m/s",
"type": "number",
"default": 1,
"minimum": 1e-6,
"maximum": 330
},
"kinematic_viscosity": {
"title": "Kinematic Viscosity",
"description": "Kinematic viscosity nu",
"type": "number",
"minimum": 1e-6,
"maximum": 0.1
},
"characteristic_length": {
"title": "Characteristic aerofoil length",
"description": "Chord length l in m",
"type": "number",
"minimum": 1e-6,
"maximum": 10
},
"mach_number": {
"title": "Mach number",
"description": "",
"type": "number",
"default": 0,
"minimum": 0,
"maximum": 0.8
},
"n_critical": {
"title": "N critical",
"description": "N critical amplification factor from eN method ",
"type": "number",
"default": 9,
"minimum": 0,
"maximum": 20
},
"re_xtr": {
"title": "Critical Reynolds number for top and bottom of the airfoil",
"description": "Reynolds number at which the transition from laminar to turbulent flow occurs [Top, Bottom]",
"type": "array",
"prefixItems": [
{
"type": "number",
"default": 5e5,
"minimum": 1e-6,
"maximum": 1e9
},
{
"type": "number",
"default": 5e5,
"minimum": 1e-6,
"maximum": 1e9
}
],
"additionalItems": false
}
}
},
"output_values_schema": {
"type": "object",
"properties": {
"reynolds_number": {
"description": "Reynolds number calculated from input parameters",
"type": "number",
"minimum": 0,
"maximum": 1000000000000
},
"cl": {
"description": "Output Cl values corresponding to the input alpha values",
"type": "array",
"title": "Cl values",
"items": {
"type": "number"
}
},
"cd": {
"description": "Output Cd values corresponding to the input alpha values",
"type": "array",
"title": "Cd values",
"items": {
"type": "number"
}
},
"cm": {
"description": "Output Cm values corresponding to the input alpha values",
"type": "array",
"title": "Cm values",
"items": {
"type": "number"
}
},
"cp_min": {
"description": "Min Cp values corresponding to the input alpha values",
"title": "Min Cp values",
"type": "array"
},
"cp": {
"description": "Cp values for x and y coordinate of the airfoil",
"title": "Cp values",
"type": "array"
}
}
}
}