toolParameters Element |
Parameters for the HandbookAero tool
Namespace: Empty
Schema: Empty
Name | Occurrences | Description |
---|---|---|
All | ||
dataInsertionMode | Way of insertion for results. add=adding computed results to existing values subtract=subtracting computed results from existing values replace=replacing existing values by computed results | |
logLevel | Detail level of handbookAero logging | |
modifyByFormula | [0, 1] | Parameters and options for the modification of aerodynamic data by formulas |
viscousDrag | [0, 1] | List of available methods for computing viscous drag |
wingPaneling | Approx. [Value * 5 + Number of spanwise segments (including additional segments due to control surfaces)] spanwise panels. If the wing is symmetric, this values is used for one side. |
Name | Type | Required | Description |
---|---|---|---|
externalDataDirectory | string | ||
externalDataNodePath | string | ||
externalFileName | string |
Parameters and options for the HandbookAero tool.
Way of insertion for results. There are three options available:
Detail level of handbookAero logging. There are three options available:
This node contains a parameter for the fineness of the wing paneling. The value is used as common value for all wings. In case of <loadCases> runmode, and if already existing spanwise distributions are provided, this provided paneling is used instead.
This node contains the available methods and their parameters for calculating the viscous drag.
This node contains the parameters for creating or modifying data by specified formulas.