liftingLine Element

LIFTING_LINE tool data

Namespace: Empty

Schema: Empty

Type
Parents
Children
NameOccurrencesDescription
Sequence Sequence
      Element tool

Tool identification

      Element aircraftModelUID

Reference to aircraft model

      Element datasetName[0, 1]

Name of the dataset for LIFTING_LINE calculation

      Element referenceValues[0, 1]

Reference values for aerodynamic computations

      Choice Choice
            Element loadCases

Data for loadcase computation

            Element performanceMap

Parameters for computation of aerodynamic performance maps

      Element toolParameters

Parameters for LIFTING_LINE tool control

Attributes
NameTypeRequiredDescription
Attribute externalDataDirectorySimple Type string
Attribute externalDataNodePathSimple Type string
Attribute externalFileNameSimple Type string
Remarks

0. General overview

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 .

  • Framework integration is the typical way, how LIFTING_LINE is used via an integration framework. Reference values are taken from the selected aircraft model's <reference> node and operating conditions are specified as links to the corresponding definitions in the selected aircraft model as well. During the input mapping phase (which is done in framework integration before the toolwrapper itself is started), reference values and operating conditions are copied into this toolspecific block to create a valid Toolwrapper input dataset for the toolwrapper itself.
  • Toolwrapper input is the required input dataset for the LIFTING_LINE toolwrapper. It is either created by the integration framework (see above), or - if the toolwrapper is used as a stand-alone program (to create LIFTING_LINE input datasets more easily) - it has to be provided by the user.

1. <tool> (mandatory)

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.

2. <aircraftModelUID> (mandatory)

Unique identifier (UID) of the aircraft model to be analyzed.

3. <datasetName> (optional)

Name of the dataset (used during LIFTING_LINE computation only). If this node is missing, the CPACS dataset name is used as default.

4. <referenceValues> (Toolwrapper input only, mandatory)

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).

5. Either <loadCases>or <performanceMaps> (mandatory)

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).

6. <toolParameters> (mandatory)

In this node, all the control parameters for LIFTING_LINE are specified.

See Also