Large Airfoil Model (LAM) is a machine learning airfoil aerodynamics analysis tool, trained on strictly experimental data. It can be used to predict airfoil surface pressure distributions, integrated force and moment coefficients, including their uncertainties.
As a probabilistic model, LAM has incorporated the experimental uncertainties from each source material for inference.
Features
Prediction of airfoil pressure, integrated force, and moment coefficients including the uncertainty at various Mach numbers and angles of attack
Significantly faster computation time than traditional Navier-Stokes solvers
Accurate prediction of complex aerodynamic phenomena (e.g. compressibility effects, flow separation) compared to low-fidelity potential flow solvers
Live visualization of your results online
How to use via the Large Airfoil Model Digital Assistant (LAM-DA)
Ask LAM-DA any question regarding airfoil aerodynmics using natural language!
For an inquiry about a specific airfoil, please make sure to include the airfoil name, angle of attack, and Mach number information in your prompt.
Current capabilities:
Retrieval of existing airfoil pressure distribution data from the ASPIRE database
Prediction of airfoil pressure distribution using the LAM
Prediction of integrated force and moment coefficients
Visualization of airfoil coordinates
Response to general airfoil inquiries
Upcoming features:
Retention of memory of the on-going conversation (coming soon!)
Provide attachment of airfoil geometry as CSV (coming soon!)
Inverse airfoil design based on user's natural language query
Identify and analyze flow features from the \(C_p\) distributions
Improvement of model robustness
How to use via manual coordinate input to
Navigate to the "ADAPT" tab of the website.
Select or manually enter the coordinates of the airfoil that you want to analyze (CSV input wil be available in the future).
Enter the target Mach number and angle of attack.
(Optional) Choose the resolution output \(C_p\) distribution.
Click "Analyze."
Hello, my name is LAM-DA. How may I assist you today?
Here are some sample questions for you to get started:
What is the SC1095 airfoil Cp distribution at Mach 0.6 and angle of attack of 6.2 degrees?
Please predict the Cp of the RAE2822 airfoil at Mach 0.73 and angle of attack of 3 degrees.
