Virginia Tech® home

Air-Breathing Propulsion Calculator

Air-Breathing Propulsion Calculator

HTML-based design aerothermodynamic analysis
Exhaust view of TFE731 engine at Virginia Tech

This calculator was created by Evan Warner while a student in AOE 3164 Aerothermodynamics and Propulsion at Virginia Tech.

The calculator concept was inspired by the Compressible Aerodynamics Calculator created by Prof. William Devenport.

Documentation of the theory, assumptions, and formulae implemented in the calculator is available to follow:

*
Online_Propulsion_Calculator_Evan Warner_V3.pdf Background, theory and technical details for the calculator. By Evan Warner.
Download File

Air-Breathing Propulsion Calculator
Calculates Performance Values for Ramjet, Turbojet, Turbofan, and Turboprop Engines

Ramjet Engine Assumptions: No Afterburner, Rprod = Rair, pe = pa
DESIGN PARAMETERS:
  • T04 (K) =
  • Ma =
  • QR (J/kg) =
FLIGHT CONDITIONS:
  • Ta (K) =
  • pa (Pa) =
  • Rair (J/kg/K)=
  • γa =
IDEAL or REAL:
ENGINE PARAMETERS (if IDEAL, no need to fill in engine parameters):
  • γd =
  • rd (p02/p0a) =
  • γb =
  • rb (p04/p03) =
  • γn =
  • rn (p0e/p06) =
PERFORMANCE VALUES (Press "CLEAR" before next calculation)
  • ST (N/(kg/s)) =
  • TSFC ((kg/s)/N) =
  • ηp =
  • ηth =
  • η0 =
Turbojet Engine Assumptions: No Afterburner, Rprod = Rair, pe = pa
DESIGN PARAMETERS:
  • T04 (K) =
  • Ma =
  • prc =
  • QR (J/kg) =
FLIGHT CONDITIONS:
  • Ta (K) =
  • pa (Pa) =
  • Rair (J/kg/K)=
  • γa =
IDEAL or REAL:
ENGINE PARAMETERS (if IDEAL, no need to fill in engine parameters):
  • γd =
  • ηd =
  • γc =
  • ηc =
  • γb =
  • ηb =
  • γt =
  • ηt =
  • γn =
  • ηn =
PERFORMANCE VALUES (Press "CLEAR" before next calculation)
  • ST (N/(kg/s)) =
  • TSFC ((kg/s)/N) =
  • ηp =
  • ηth =
  • η0 =
Turbofan Engine Assumptions: No Afterburner, Rprod = Rair, pe = pa
DESIGN PARAMETERS:
  • T04 (K) =
  • Ma =
  • prc =
  • prf =
  • ℬ =
  • QR (J/kg) =
FLIGHT CONDITIONS:
  • Ta (K) =
  • pa (Pa) =
  • Rair (J/kg/K)=
  • γa =
IDEAL or REAL:
ENGINE PARAMETERS (if IDEAL, no need to fill in engine parameters):
  • γd =
  • ηd =
  • γc =
  • ηc =
  • γb =
  • ηb =
  • γt =
  • ηt =
  • γn =
  • ηn =
  • γf =
  • ηf =
  • γnf =
  • ηnf =
PERFORMANCE VALUES (Press "CLEAR" before next calculation)
  • ST (N/(kg/s)) =
  • TSFC ((kg/s)/N) =
  • ηp =
  • ηth =
  • η0 =
Turboprop Engine Assumptions: No Afterburner, Rprod = Rair, pe = pa
DESIGN PARAMETERS:
  • T04 (K) =
  • Ma =
  • prc =
  • QR (J/kg) =
FLIGHT CONDITIONS:
  • Ta (K) =
  • pa (Pa) =
  • Rair (J/kg/K)=
  • γa =
IDEAL or REAL:
ENGINE PARAMETERS (if IDEAL, no need to fill in engine parameters):
  • γd =
  • ηd =
  • γc =
  • ηc =
  • γb =
  • ηb =
  • γt =
  • ηt =
  • γn =
  • ηn =
  • γf =
  • ηf =
  • γnf =
  • ηnf =
TURBOPROP CHARACTERISTICS (if IDEAL, no need to fill in)
  • ηprop =
  • ηpt =
  • ηg =
PERFORMANCE VALUES (Press "CLEAR" before next calculation)
  • ST (N/(kg/s)) =
  • TSFC ((kg/s)/N) =
  • ηp =
  • ηth =
  • η0 =
OPTIMAL THRUST SPLIT
  • Thrust Contribution from Propeller (%) =
  • Thrust Contribution from Core (%) =
Javascript, HTML, and CSS by Evan Warner,
Student of Aerospace Engineering with the Department of Aerospace and Ocean Engineering at Virginia Tech.
Last updated on March 31st, 2022.
Please send any questions, comments, or suggestions to: Evan Warner (evanpw3@vt.edu)