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De Laval Supersonic Convergent-Divergent Nozzle Mass Flow Calculator

Easily calculate and compute de laval supersonic convergent-divergent nozzle mass flow calculator with accurate equations, live formulas, and expert guidance.

Minimum neck cross-sectional area.

Total pressure upstream of nozzle entrance.

Combustion chamber stagnation temperature.

Combustion gas heat capacity ratio.

Gas constant (e.g. ~365 J/(kg*K) for rocket propellants, 287 for air).

Calculated Result
82.6 kg/s

Choked Mass Flow

Choked Mass Flow

82.6 kg/s

Choked Mass Flow Rate Kg S

82.6

Throat Static Pressure Bar

13.87

Critical Choking Pressure Ratio

0.555

Characteristic Velocity C Star Ms

1362

82.6 — kg/s

Calculation Breakdown

  1. Applied FormulaCalculates sonic choked mass flow rate and characteristic velocity c* for convergent-divergent supersonic De Laval nozzles.\dot{m} = \frac{P_0 A^*}{\sqrt{T_0}} \Gamma(\gamma, R), \quad \frac{P^*}{P_0} = \left(\frac{2}{\gamma+1}\right)^{\frac{\gamma}{\gamma-1}}

De Laval Nozzle Flow Metric Output

Interactive visualization based on your current inputs

Calculated Value
0.021416283Choked Mass Flow

What Is the De Laval Supersonic Convergent-Divergent Nozzle Mass Flow Calculator?

This tool computes de laval supersonic convergent-divergent nozzle mass flow calculator with high precision arithmetic.

How Does the De Laval Supersonic Convergent-Divergent Nozzle Mass Flow Calculator Work?

Calculates sonic choked mass flow rate and characteristic velocity c* for convergent-divergent supersonic De Laval nozzles.

De Laval Supersonic Convergent-Divergent Nozzle Mass Flow Calculator Formula & Variables

The core mathematical equation utilized by this calculator is expressed as:

m˙=P0A∗T0Γ(γ,R),P∗P0=(2γ+1)γγ−1\dot{m} = \frac{P_0 A^*}{\sqrt{T_0}} \Gamma(\gamma, R), \quad \frac{P^*}{P_0} = \left(\frac{2}{\gamma+1}\right)^{\frac{\gamma}{\gamma-1}}

Calculates sonic choked mass flow rate and characteristic velocity c* for convergent-divergent supersonic De Laval nozzles.

How to Use the De Laval Supersonic Convergent-Divergent Nozzle Mass Flow Calculator

  1. Enter your parameters into the designated input fields to calculate the result immediately.

Step-by-Step Example Calculation

De Laval Supersonic Convergent-Divergent Nozzle Mass Flow Calculator Example

Input Values:

throatAreaAtM2:0.045
stagnationPressureP0Bar:25.0
stagnationTemperatureT0K:2200.0
specificHeatRatioGamma:1.25
gasConstantRJPerKgK:365.0
Worked Steps: Sample evaluation based on standard reference conditions.

Understanding Your Result

The calculated primary figure indicates the optimal or required kg/s.

Factors That Affect the Result

  • Measurement tolerances, operational variance, and real-world conditions.

When Should You Use This Calculator?

  • Everyday budgeting, technical homework, professional estimation, and household projects.

Assumptions & Limitations

  • Assumes standard atmospheric or environmental parameters unless specified.

Frequently Asked Questions

Calculation Accuracy & Reference Note

Double-precision IEEE 754 arithmetic with validated empirical constants.

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