liftingLine Element |
LIFTING_LINE 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 LIFTING_LINE calculation |
referenceValues | [0, 1] | Reference values for aerodynamic computations |
Choice | ||
loadCases | Data for loadcase computation | |
performanceMap | Parameters for computation of aerodynamic performance maps | |
toolParameters | Parameters for LIFTING_LINE tool control |
Name | Type | Required | Description |
---|---|---|---|
externalDataDirectory | string | ||
externalDataNodePath | string | ||
externalFileName | string |
Toolspecific data for the LIFTING_LINE tool. LIFTING_LINE is basically an incompressible, inviscid 3D lifting line method for aerodynamic computations based on the potential flow equations. An additional compressibility correction allows for LIFTING_LINE to be used in the compressible flight range as well. LIFTING_LINE neglects wing thickness and does not cover transonic effects. Optionally, the LIFTING_LINE results can be processed through the 2.5 D polar interpolation tool POLINT. Providing suitable 2D airfoil polars, covering the required range of operating conditions, the user can utilize POLINT in order to cover thickness and transonic effects as well.
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 "LIFTING_LINE", the <version> subnode contains the used toolversion in the form "#x.#y.#z" with "#x.#y" as LIFTING_LINE version number and "#z" as number of the corresponding LIFTING_LINE toolwrapper.
Unique identifier (UID) of the aircraft model to be analyzed.
Name of the dataset (used during LIFTING_LINE computation only). If this node is missing, the CPACS dataset name is used as default.
Set of reference values used for LIFTING_LINE 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 all three LIFTING_LINE reference lengths).
These nodes contain the operating conditions of the aircraft for the LIFTING_LINE computations. LIFTING_LINE 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 LIFTING_LINE are specified.