| flow Element |
This type contains a complete set of flow condition data
Namespace: Empty
Schema: Empty
Type
ParentsChildren| Name | Occurrences | Description |
|---|---|---|
 Sequence | ||
 Choice | ||
| Sequence | ||
 airspeed | Airspeed | |
| Choice | ||
| Sequence | ||
| kinematicViscosity | Kinematic Viscosity | |
| speedOfSound | Speed of Sound | |
| Sequence | ||
| standardAltitude | Standard Altitude | |
| deltaTemperature | [0, 1] | Temperature offset from standard atmosphere |
| Sequence | ||
| reynoldsNumber | Reynolds Number | |
| Choice | ||
| Sequence | ||
| speedOfSound | Speed of Sound | |
| Choice | ||
| airspeed | Airspeed | |
| kinematicViscosity | Kinematic Viscosity | |
| Sequence | ||
| standardAltitude | Standard Altitude | |
| deltaTemperature | [0, 1] | Temperature offset from standard atmosphere |
| Sequence | ||
| machNumber | Mach Number | |
| Choice | ||
| Sequence | ||
| kinematicViscosity | Kinematic Viscosity | |
| Choice | ||
| airspeed | Airspeed | |
| speedOfSound | Speed of Sound | |
| Sequence | ||
| standardAltitude | Standard Altitude | |
| deltaTemperature | [0, 1] | Temperature offset from standard atmosphere |
| reynoldsNumber | Reynolds Number | |
| angleOfYaw | Yaw angle | |
| Choice | ||
| angleOfAttack | Angle of attack | |
| targetLiftCoefficient | Target Lift Coefficient | |
| quasiSteadyRotation | [0, 1] | This type defines a set of quasi steady rotations. |
| controlSurfaces | [0, 1] | This type contains a list of deflected control surfaces |
Attributes| Name | Type | Required | Description |
|---|---|---|---|
 externalDataDirectory |  string | ||
| externalDataNodePath | string | ||
| externalFileName | string |
Remarks0. General overview
All the flow parameters for the aerodynamic computations are defined in this type.
1. Mach number and Reynolds number (mandatory)
The aerodynamic computations are executed, based on the nondimensional similarity parameters Mach number and Reynolds number . Using the ISA (ICAO Standard Atmosphere), extended by an optional temperature offset, these parameters can be specified in several different ways (see point 1)
- <mach number> & <reynoldsNumber>
- <mach number> & <standardAltitude> (optionally: & <deltaTemperature>)
- <mach number> & <kinematicViscosity> & <airspeed>
- <mach number> & <kinematicViscosity> & <speedOfSound>
- <reynoldsNumber> & <standardAltitude> (optionally: & <deltaTemperature>)
- <reynoldsNumber> & <speedOfSound> & <airspeed>
- <reynoldsNumber> & <speedOfSound> & <kinematicViscosity>
- <airspeed> & <standardAltitude> (optionally: & <deltaTemperature>)
- <airspeed> & <kinematicViscosity> & <speedOfSound>
2. <angleOfYaw> (mandatory)
This is the angle of yaw for the loadcase. A positive angle of yaw means that the model is rotated around the z-axis by a positive value with respect to the incoming flow. So for the model, the flow comes from front-starboard side then.
3. <angleOfAttack> or <targetLiftCoefficient> (mandatory)
<angleOfAttack> is the angle of attack for the loadcase. A positive angle of attack means that the model is rotated around the y-axis by a positive value with respect to the incoming flow. So for the model, the flow comes from front-below then. Alternatively, a <targetLiftCoefficient> can be specified. In this case, the <angleOfAttack> is iterated automatically, so that the given lift coefficient (C Fz ) is met.
4. <quasiSteadyRotation> (optional)
If this node is specified, the steady flow described above is superseded with a set of quasi steady rotations.
5. <controlSurfaces> (optional)
If this node is specified, the flow described above is computed on an aircraft configuration with a set of deflected control surfaces.
See Also