Thermodynamic Calculations for Rocket Engines (Termodinamicheskiy Raschet Raketnykh)

Abstract

This book presents an approximate method for the calculation of thermodynamic parameters of the products of combustion in a rocket engine, as well as a method for the calculation of the specific thrust, without a determination of the composition of the products of combustion. The proposed method will make it possible to calculate these parameters with relatively little effort but with a sufficient degree of accuracy from the practical standpoint. This method is valid for the products of combustion of fuels composed of C, H, N, and O, with some reservations with regard to the method for the latter. Examples of the calculations are presented. In addition, there is a description of a method for the determination of the composition of the products of combustion from the indicated fuels.

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Document Details

Document Type
Technical Report
Publication Date
Jun 15, 1962
Accession Number
AD0277653

Entities

People

  • B.a. Nikolayev

Organizations

  • Air Force Systems Command

Tags

DTIC Thesaurus Topics

  • Accuracy
  • Carbon Dioxide
  • Chemical Composition
  • Chemical Elements
  • Chemical Reactions
  • Chemistry
  • Combustion
  • Combustion Chambers
  • Combustion Products
  • Dielectric Gases
  • Dissociation
  • Enthalpy
  • Heat Of Combustion
  • Materials Science
  • Partial Pressure
  • Rocket Engines
  • Thermodynamics

Fields of Study

  • Physics

Readers

  • Combustion science or combustion engineering.
  • Systems Analysis and Design