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Table 1
Description of the main parameters and where they are defined.
| Synthetic models | ||
| a | bending of the boundarySect. 4.5 | |
| b | aspect ratio of the boundaryFig. 2 | |
| Baxis | field strength on the flux rope axisSect. 3.1 | |
| c | Bz for A = 1,Eq. (4) | |
|
={ a,b,n,rBmin,ωmin }, set of all characteristics | |
| of a model and selection parametersEq. (8) | ||
| n | exponent defining Bz and jzEqs. (4), (5) | |
| x | coordinate along the simulated trajectoryFig. 2 | |
| y | coordinate across the simulated trajectoryFig. 2 | |
| z | coordinate along the flux rope axisSect. 3.1 | |
| y/b | true impact parameterFig. 2 | |
| Fitted Lundquist model | ||
| α | linear force-free field constantEq. (1) | |
| B L | Lundquist fieldEq. (1) | |
| B 0 | estimated axial field strengthEq. (1) | |
| dev | function of fit minimizationEq. (2) | |
| R | flux rope radius (for Bz = 0)Fig. 2 | |
| y L | estimated distance of the spacecraft trajectoryFig. 2 | |
| to the flux rope axis | ||
| p | =yL/R, estimated impact parameterFig. 2 | |
| Estimated along the spacecraft trajectory | ||
| ⟨ B⟩ | average B strengthSect. 3.2 | |
| ⟨ Bx⟩ | average B component parallel to the spacecraftSect. 4.1 | |
| trajectory | ||
| r Bx | =⟨ Bx⟩ / ⟨B⟩Sect. 4.1 | |
| ω | rotation angle of B across the flux ropeSect. 3.3 | |
| Selection parameters | ||
| r Bmin | minimum average field strength to detect | |
| a flux rope: ⟨ B⟩ /Baxis ≥ rBminSect. 4.4 | ||
| ω min | minimum rotation angle of B to detect a flux rope Sect. 4.4 | |
| Probability functions | ||
|
observed probabilityFig. 1 | |
|
theoretical probability for a model defined by Eq. (8) |
|
|
integrated on a flux rope setEq. (9) |
|
| P(b) | probability distribution of bEq. (9) | |
| b mean | mean value of bEqs. (12), (13) | |
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