Normal Shock
Calculate property changes across a normal shock wave in supersonic flow. Normal shocks occur when supersonic flow encounters an obstruction, resulting in a sudden change in flow properties.
Upstream Flow (State 1)
Downstream Flow (State 2)
Shock Wave Effects
Normal Shock Visualization
Hover upstream, downstream, or the shock wave to highlight the corresponding values.
Normal Shock Details
Hover over the visualization to explore shock properties
Open Source and Easy to Use Elsewhere
This tool is open source and the underlying logic is fully transparent. You can inspect the code, understand the calculations, and contribute improvements. If you want to use the tool in your own website, course page, or learning platform, you can also embed it directly and start from a ready-made iframe setup for this exact tool.
Open source: review the implementation and see how the results are produced.
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