SISSAmathLab/airfoil-transonic-internal

Airfoil Transonic Flow - Internal Domain Dataset

Dataset Description

This dataset contains transonic flow simulations around an airfoil, focusing on internal flow field quantities with varying angle of attack.

Dataset Summary

The Airfoil Transonic Internal dataset provides numerical simulations of compressible transonic flow around an airfoil profile. The dataset focuses on aerodynamic quantities in the flow field surrounding the airfoil, including pressure and velocity distributions in the computational domain, making it valuable for flow field analysis, aerodynamic research, and machine learning applications in computational fluid dynamics.

Dataset Structure

Data Instances

The dataset consists of three configurations:

• geometry: Internal domain node coordinates
• snapshots: Flow field solutions in the domain
• parameters: Flow condition parameters (angle of attack)

Data Fields

Geometry Configuration

• node_coordinates_x: Sequence of x-coordinates of internal domain nodes (float64)
• node_coordinates_y: Sequence of y-coordinates of internal domain nodes (float64)

Snapshots Configuration

• pressure: Pressure field in the internal domain (float64)
• velocity: Velocity magnitude field in the internal domain (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 simulations capture the complex flow phenomena in the transonic regime, including shock waves and expansion regions.

Preprocessing

Internal domain quantities (flow field around the airfoil, excluding the boundary) are included in this dataset. Solutions are stored as 1D arrays corresponding to the nodes in the computational mesh.

Usage

from datasets import load_dataset
import numpy as np
import matplotlib.pyplot as plt

# Load geometry
ds_geom = load_dataset("SISSAmathLab/airfoil-transonic-internal", name="geometry")

# Load snapshots
ds_data = load_dataset("SISSAmathLab/airfoil-transonic-internal", name="snapshots")

# Load parameters
ds_params = load_dataset("SISSAmathLab/airfoil-transonic-internal", name="parameters")

# Visualize pressure field in internal domain
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, 6))
plt.scatter(pts_x, pts_y, c=pressure, cmap='RdBu_r', s=1, alpha=0.6)
plt.colorbar(label='Pressure')
plt.title(f'Airfoil Flow Field (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 Boundary dataset for aerodynamic quantities specifically at the airfoil surface.