vSAero Element |
VSAero tool data
Namespace: Empty
Schema: Empty
Name | Occurrences | Description |
---|---|---|
Sequence | ||
tool | Tool identification | |
aircraftModelUID | Reference to aircraft model | |
datasetName | [0, 1] | Name of the dataset for VSAero calculation |
referenceValues | [0, 1] | Reference values for VSAero computation |
Choice | ||
loadCases | Data for loadcase computation | |
performanceMap | Parameters for computation of aerodynamic performance maps | |
toolParameters | Parameters for VSAero tool control |
Name | Type | Required | Description |
---|---|---|---|
externalDataDirectory | string | ||
externalDataNodePath | string | ||
externalFileName | string |
Toolspecific data for the commercial VSAero tool. VSAero is basically an incompressible, inviscid 3D panel code for aerodynamic computations based on the potential flow equations. Additional compressibility correction and boundary layer computation allow for VSAero to be used in the compressible flight range and to incorporate viscous drag as well. VSAero does not cover transonic effects.
In this toolspecific data block, two ways of input definition are possible: Framework integration and Toolwrapper input .
Identification of the tool. The <name> subnode is always "VSAero", the <version> subnode contains the used toolversion in the form "#x.#y.#z" with "#x.#y" as VSAero version number and "#z" as number of the corresponding VSAero toolwrapper.
Unique identifier (UID) of the aircraft model to be analyzed.
Name of the dataset (used during VSAero computation only). If this node is missing, the CPACS dataset name is used as default.
Set of reference values used for VSAero computations. This node is required for the Toolwrapper input only. In Framework integration, these values are taken form the specified aircraft model's <reference> node (using <length> for both VSAero reference lengths).
These nodes contain the operating conditions of the aircraft for the VSAero computations. VSAero distinguishes between two runmodes: <loadCases> and <performanceMaps> . In <loadCases> mode, a set of individual loadcases is computed. In <performanceMaps> mode, an aerodynamic performance map over a sweep of Mach- and Reynolds-numbers, angles of yaw and of attack is created (optionally extended by delta-performance maps for control surfaces and damping derivatives).
In this node, all the control parameters for VSAero are specified.