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dataset_info:
- config_name: geometry
features:
- name: node_coordinates_x
list: float64
- name: node_coordinates_y
list: float64
splits:
- name: default
num_bytes: 7176
num_examples: 1
download_size: 8275
dataset_size: 7176
- config_name: parameters
features:
- name: angle_of_attack
dtype: float64
splits:
- name: default
num_bytes: 800
num_examples: 100
download_size: 1465
dataset_size: 800
- config_name: snapshots
features:
- name: pressure
list: float64
- name: wall_shear_stress
list: float64
splits:
- name: default
num_bytes: 717600
num_examples: 100
download_size: 810975
dataset_size: 717600
configs:
- config_name: geometry
data_files:
- split: default
path: geometry/default-*
- config_name: parameters
data_files:
- split: default
path: parameters/default-*
- config_name: snapshots
data_files:
- split: default
path: snapshots/default-*
---
# Airfoil Transonic Flow - Boundary Dataset
## Dataset Description
This dataset contains transonic flow simulations around an airfoil, focusing on boundary (airfoil surface) quantities with varying angle of attack.
### Dataset Summary
The Airfoil Transonic Boundary dataset provides numerical simulations of compressible transonic flow around an airfoil profile. The dataset focuses on aerodynamic quantities at the airfoil surface (boundary), including pressure and wall shear stress distributions, making it valuable for aerodynamic analysis, design optimization, and machine learning applications in aerospace engineering.
## Dataset Structure
### Data Instances
The dataset consists of three configurations:
- **geometry**: Airfoil surface node coordinates
- **snapshots**: Aerodynamic field solutions at the boundary
- **parameters**: Flow condition parameters (angle of attack)
### Data Fields
#### Geometry Configuration
- `node_coordinates_x`: Sequence of x-coordinates of airfoil surface nodes (float64)
- `node_coordinates_y`: Sequence of y-coordinates of airfoil surface nodes (float64)
#### Snapshots Configuration
- `pressure`: Pressure distribution along the airfoil surface (float64)
- `wall_shear_stress`: Wall shear stress distribution along the airfoil surface (float64)
#### Parameters Configuration
- `angle_of_attack`: angle of attack for each simulation (float64)
### Data Splits
- `default`: Contains all simulations with varying angle of attack
## Dataset Creation
### Source Data
The dataset was generated using computational fluid dynamics simulations of the Euler equations for compressible transonic flow around an airfoil. The transonic regime is characterized by mixed subsonic and supersonic flow regions, often exhibiting shock waves.
### Preprocessing
Only boundary quantities (at the airfoil surface) are included in this dataset. Solutions are stored as 1D arrays corresponding to the nodes on the airfoil surface.
## Usage
```python
from datasets import load_dataset
import numpy as np
import matplotlib.pyplot as plt
# Load geometry
ds_geom = load_dataset("SISSAmathLab/airfoil-transonic-boundary", name="geometry")
# Load snapshots
ds_data = load_dataset("SISSAmathLab/airfoil-transonic-boundary", name="snapshots")
# Load parameters
ds_params = load_dataset("SISSAmathLab/airfoil-transonic-boundary", name="parameters")
# Visualize pressure distribution on airfoil surface
pts_x = np.asarray(ds_geom['default']['node_coordinates_x']).flatten()
pts_y = np.asarray(ds_geom['default']['node_coordinates_y']).flatten()
pressure = ds_data['default']['pressure'][0]
angle_of_attack = ds_params['default']['angle_of_attack'][0]
plt.figure(figsize=(12, 4))
plt.scatter(pts_x, pts_y, c=pressure, cmap='RdBu_r', s=20)
plt.colorbar(label='Pressure')
plt.title(f'Airfoil Surface Pressure (angle of attack={angle_of_attack:.2f})')
plt.xlabel('x')
plt.ylabel('y')
plt.axis('equal')
plt.grid(True, alpha=0.3)
plt.show()
```
## Related Datasets
See also: **Airfoil Transonic Internal** dataset for flow field quantities in the internal domain around the airfoil.
## Contact
For questions or issues, please contact SISSA mathLab. |