Nozzle Area Mach Number Calculator
Solve both subsonic and supersonic isentropic Mach branches for an entered area-to-sonic-area ratio.
YOUR CALCULATION
Result
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Calculation steps
Work through one step at a time or reveal the complete calculation. The steps use your current inputs.
How to calculate
Solve the monotone subsonic and supersonic branches separately, treating the sonic ratio-one case explicitly.
A/A*=(1/M)[2/(γ+1)(1+(γ−1)M²/2)]^((γ+1)/(2(γ−1)))
Worked example
At A/A*=2 and γ=1.4, the subsonic branch is about 0.305903834 and the supersonic branch about 2.19719812.
Assumptions and input details
Ideal one-dimensional isentropic perfect-gas flow. Area alone does not select the physical branch; back pressure, shocks, nozzle starting and viscous/real-gas behavior are excluded.
References: NASA Glenn: nozzle area and Mach relation
Using this calculator
Can I enter my own problem?
Yes. Replace the example values with your own inputs. The result, calculation steps, tables and applicable diagrams update from those inputs. Blank or invalid values clear the result; example values are never silently substituted for missing inputs.
Are the results exact?
Results use floating-point arithmetic and displayed rounding. Read the formula, assumptions and any stated data precision before interpreting the result.
Is my input uploaded?
The calculation runs in your browser. No account, file upload or external AI service is required. Inputs are not saved between page reloads.
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