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Supersonic Aero-Engine Convergent-Divergent (de Laval) Nozzle Thrust & Under/Over-Expansion Calculator

Easily calculate and compute supersonic aero-engine convergent-divergent (de laval) nozzle thrust & under/over-expansion calculator with accurate equations, live formulas, and expert guidance.

Calculated Result
171.7 kN

Total Gross Jet Thrust (F_gross)

Total Gross Jet Thrust (F_gross)

171.7 kN

Exit Mach Number

1.51

Exit Static Pressure Bar

3.862

Exhaust Velocity M Per S

1111

Expansion Regime

UNDER-EXPANDED (Expansion fans at lip)

171.7 — kN

Calculation Breakdown

  1. Applied FormulaCalculates de Laval rocket and supersonic fighter engine nozzle exit Mach, under-expansion/over-expansion pressure thrust, and total gross propulsion.F_g = \dot{m} v_e + (p_e - p_a) A_e, \quad \frac{A_e}{A^*} = \frac{1}{M_e}\left[\frac{2}{\gamma+1}\left(1 + \frac{\gamma-1}{2}M_e^2\right)\right]^{\frac{\gamma+1}{2(\gamma-1)}}

Supersonic CD Nozzle Thrust Metric Output

Interactive visualization based on your current inputs

Calculated Value
0.04386129172Total Gross Jet Thrust (F_gross)

What Is the Supersonic Aero-Engine Convergent-Divergent (de Laval) Nozzle Thrust & Under/Over-Expansion Calculator?

This tool computes supersonic aero-engine convergent-divergent (de laval) nozzle thrust & under/over-expansion calculator with high precision arithmetic.

How Does the Supersonic Aero-Engine Convergent-Divergent (de Laval) Nozzle Thrust & Under/Over-Expansion Calculator Work?

Calculates de Laval rocket and supersonic fighter engine nozzle exit Mach, under-expansion/over-expansion pressure thrust, and total gross propulsion.

Supersonic Aero-Engine Convergent-Divergent (de Laval) Nozzle Thrust & Under/Over-Expansion Calculator Formula & Variables

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

Fg=m˙ve+(pe−pa)Ae,AeA∗=1Me[2γ+1(1+γ−12Me2)]γ+12(γ−1)F_g = \dot{m} v_e + (p_e - p_a) A_e, \quad \frac{A_e}{A^*} = \frac{1}{M_e}\left[\frac{2}{\gamma+1}\left(1 + \frac{\gamma-1}{2}M_e^2\right)\right]^{\frac{\gamma+1}{2(\gamma-1)}}

Calculates de Laval rocket and supersonic fighter engine nozzle exit Mach, under-expansion/over-expansion pressure thrust, and total gross propulsion.

How to Use the Supersonic Aero-Engine Convergent-Divergent (de Laval) Nozzle Thrust & Under/Over-Expansion Calculator

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

Step-by-Step Example Calculation

Supersonic Aero-Engine Convergent-Divergent (de Laval) Nozzle Thrust & Under/Over-Expansion Calculator Example

Input Values:

nozzleThroatAreaCm2:850
nozzleExitAreaCm2:1550
totalChamberPressureBar:14
totalChamberTempK:1950
ambientStaticPressureBar:0.45
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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