For Researchers · Airfoil Lift & Drag
Airfoil Lift & Drag for a launch abort
Built for researchers prototyping or validating an idea. Prototype fast, reproduce exactly, and share a citable, interactive version of your model. Simulate a launch abort live below — adjust the inputs and watch it respond, right in your browser.
Airfoil Lift & DragLive
the wing's polar
Controls
Presets
Lift rises almost linearly with angle of attack — until the airflow separates and the wing stalls, losing lift sharply. Drag has a fixed part plus induced drag that grows with lift squared and shrinks with aspect ratio. The lift-to-drag ratio, peaking at a modest angle, is the single number that governs a wing's efficiency.
Data Inspector
Lift coeff. CL0.53
Drag coeff. CD0.033
Lift/Drag16.0
Statusattached
Governing equation
Reading this result: Pre-stall: lift rises almost linearly with angle of attack at 6°, well below the ~15° stall angle. Adding camber would lift the entire curve higher.
Runs locally in your browser — free forever. Scale to the cloud when reality gets heavy.
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Frequently asked questions
- Is this good for researchers?
- Yes — this version of "Airfoil Lift & Drag for a launch abort" is framed for researchers prototyping or validating an idea. Prototype fast, reproduce exactly, and share a citable, interactive version of your model.
- Do I need to install anything?
- No. It runs in any modern browser, free, with no account required.