Update README.md

README.md

@@ -29,7 +29,7 @@ ensures greater diversity than existing ones. Please refer to our [arXiv paper](
    |39-56| Mach numbers and angles of attacks |
    
 2. Index file
-  `index.npy` provides the crucial information for all provided samples; it has a shape of $28856 \times 8$, with each channel listed below:
+  `index.npy` provides the crucial information for all provided samples; it has a shape of \\( 28856 \times 8 \\), with each channel listed below:
 
    |index|description|
    |-|-|
@@ -44,15 +44,15 @@ ensures greater diversity than existing ones. Please refer to our [arXiv paper](
    |8|pitching moment coefficient|
   
 3. Reference surface mesh and surface physical quantities on this reference mesh
-   The reference mesh `geom0` contains the cell-centric coordinates of the reference surface mesh with size $256 \times 128 \times 3$, and the three channels stand
-   for $x, y, z$. The surface physical quantities `data.npy` are on the same reference mesh with size $256 \times 128 \times 3$, and the three channels stand for
-   $C_p, C_{f,\tau}, C_{f,z}$.   (the latter two are the decomposed friction coefficients on the streamwise and spanwise directions). These data can serve as input and
+   The reference mesh `geom0` contains the cell-centric coordinates of the reference surface mesh with size \\( 256 \times 128 \times 3 \\), and the three channels stand
+   for \\( x, y, z \\). The surface physical quantities `data.npy` are on the same reference mesh with size \\( 256 \times 128 \times 3 \\), and the three channels stand for
+   \\( C_p, C_{f,\tau}, C_{f,z} \\).   (the latter two are the decomposed friction coefficients on the streamwise and spanwise directions). These data can serve as input and
    output for a machine learning model that predicts the aerodynamics of wings. 
 
    **reference mesh**: The simulation mesh on the wing surface is first interpolated to a reference mesh. In the spanwise ($j$-direction), 128 cross-sectional planes are
-   sampled with even spacing, and tips are excluded. For each cross-section ($i$-direction), a fixed set of normalized chordwise positions $$\{(x/c)_i\}$$ s is used for both 
+   sampled with even spacing, and tips are excluded. For each cross-section (i-direction), a fixed set of normalized chordwise positions \\( \{(x/c)_i\} \\) s is used for both 
    the upper and lower surfaces, and the tail edge is represented only with one cell. The reference mesh along the wing surface is then unfolded as shown below, resulting 
-   in a final vertex surface grid of $257 \times 129$ points per wing (`origingeom.npy`). This is useful when we need to calculate coefficients from the surface flow outputs.
+   in a final vertex surface grid of \\( 257 \times 129 \\) points per wing (`origingeom.npy`). This is useful when we need to calculate coefficients from the surface flow outputs.
    The cell-centric grid for the mesh is obtained just by averaging the coordinates at the four vertices.
 
    <img src="https://cdn-uploads.huggingface.co/production/uploads/6878e482bd4380c813fd99de/deWUNg0C2bxl7ZDQFfowu.png" alt="transform" width="40%">
@@ -70,7 +70,7 @@ The table below summarizes the data.
 |Surface mesh | `*\wing.xyz` | surface simulation mesh |  7.8 GB 
 |         | `origingeom.npy` | reference surface mesh (grid points) |  3.3 GB 
 |         | `geom0.npy` | reference surface mesh (cell center) |  3.3 GB   
-|Surface flow | `data.npy` | $C_p, \bm {C_f}$ at reference mesh (cell center) |  22.7 GB 
+|Surface flow | `data.npy` | \\( C_p, \bm {C_f} \\) at reference mesh (cell center) |  22.7 GB 
 |        | `*\surf.cgns` | raw surface flow output | 161.5 GB
 |Volume flow | `*\vol.cgns` | raw flow field output |  5.5 TB