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Rocket De Laval Nozzle Thrust Coefficient & Expansion Ratio Calculator

Easily calculate and compute rocket de laval nozzle thrust coefficient & expansion ratio calculator with accurate equations, live formulas, and expert guidance.

Sea level = 1.013 bar, vacuum = 0 bar.

Calculated Result
264.8 kN

Vacuum / Ambient Thrust

Vacuum / Ambient Thrust

264.8 kN

Thrust Output Kn

264.8

Thrust Coefficient Cf

1.499

Nozzle Exit Pressure Bar

0.497

Throat Area Cm2

176.7

264.8 — kN

Calculation Breakdown

  1. Applied FormulaCalculates the supersonic thrust coefficient ($C_f$), throat area, exit pressure, and net thrust generation for rocket converging-diverging (de Laval) nozzles.F = C_f A_t P_c, \quad C_f = \sqrt{\frac{2\gamma^2}{\gamma - 1} \left(\frac{2}{\gamma + 1}\right)^{\frac{\gamma+1}{\gamma-1}} \left[1 - \left(\frac{P_e}{P_c}\right)^{\frac{\gamma-1}{\gamma}}\right]} + \varepsilon \frac{P_e - P_a}{P_c}

Rocket Nozzle Thrust Metric Output

Interactive visualization based on your current inputs

Calculated Value
0.066132199265Vacuum / Ambient Thrust

What Is the Rocket De Laval Nozzle Thrust Coefficient & Expansion Ratio Calculator?

This tool computes rocket de laval nozzle thrust coefficient & expansion ratio calculator with high precision arithmetic.

How Does the Rocket De Laval Nozzle Thrust Coefficient & Expansion Ratio Calculator Work?

Calculates the supersonic thrust coefficient (CfC_f), throat area, exit pressure, and net thrust generation for rocket converging-diverging (de Laval) nozzles.

Rocket De Laval Nozzle Thrust Coefficient & Expansion Ratio Calculator Formula & Variables

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

F=CfAtPc,Cf=2γ2γ−1(2γ+1)γ+1γ−1[1−(PePc)γ−1γ]+εPe−PaPcF = C_f A_t P_c, \quad C_f = \sqrt{\frac{2\gamma^2}{\gamma - 1} \left(\frac{2}{\gamma + 1}\right)^{\frac{\gamma+1}{\gamma-1}} \left[1 - \left(\frac{P_e}{P_c}\right)^{\frac{\gamma-1}{\gamma}}\right]} + \varepsilon \frac{P_e - P_a}{P_c}

Calculates the supersonic thrust coefficient (CfC_f), throat area, exit pressure, and net thrust generation for rocket converging-diverging (de Laval) nozzles.

How to Use the Rocket De Laval Nozzle Thrust Coefficient & Expansion Ratio Calculator

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

Step-by-Step Example Calculation

Rocket De Laval Nozzle Thrust Coefficient & Expansion Ratio Calculator Example

Input Values:

chamberPressureBar:100
throatDiameterMm:150
nozzleExpansionRatioEpsilon:40
gasSpecificHeatRatioGamma:1.22
ambientPressureBar:1.013
Worked Steps: Sample evaluation based on standard reference conditions.

Understanding Your Result

The calculated primary figure indicates the optimal or required kN.

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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