Download or read book A General Method for Calculating the Equilibrium Compositions and Temperatures and the Thermodynamic Performance Parameters of Rocket propellant Systems written by and published by . This book was released on 1959 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt: This Report represents the current method used at the Jet Propulsion Laboratory for the determination of equilibrium compositions and temperatures and the thermodynamic performance parameters of rocket propellant systems. The method is general and is especially applicable to calculations for those propellants whose combustion products include substances (1) which may exist in pure condensed phases or in ideal solutions of such phases within the rocket chamber, or (2) for which the appearance or disappearance of such phases is possible during the expansion process. Equations are formulated in terms of fundamental quantities. The assumptions and apporximations, made to facilitate computation, are emphasized in order that the validity of calculated results may be properly evaluated.
Download or read book A General Method for Automatic Computation of Equilibrium Compositions and Theoretical Rocket Performance of Propellants written by Sanford Gordon and published by . This book was released on 1959 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt: A general computer program for chemical equilibrium and rocket performance calculations was written for the IBM 650 computer with 2000 words of drum storage, 60 words of high-speed core storage, indexing registers, and floating point attachments. The program is capable of carrying out combustion and isentropic expansion calculations on a chemical system that may include as many as 10 different chemical elements, 30 reaction products, and 25 pressure ratios. In addition to the equilibrium composition, temperature, and pressure, the program calculates specific impulse, specific impulse in vacuum, characteristic velocity, thrust coefficient, area ratio, molecular weight, Mach number, specific heat, isentropic exponent, enthalpy, entropy, and several thermodynamic first derivatives.
Download or read book NASA Technical Note written by and published by . This book was released on 1962 with total page 540 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A General IBM 704 Or 7090 Computer Program for Computation of Chemical Equilibrium Compositions Rocket Performance and Chapman Jouguet Dentonations written by Frank J. Zeleznik and published by . This book was released on 1962 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Publications of the Jet Propulsion Laboratory January 1938 Through June 1961 written by D. K. Walsh and published by . This book was released on 1961 with total page 358 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Report written by Jet Propulsion Laboratory (U.S.) and published by . This book was released on 1959 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Compilation of Thermodynamic Properties Transport Properties and Theoretical Rocket Performance of Gaseous Hydrogen written by Charles R. King and published by . This book was released on 1960 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book THEORETICAL Computations of Equilibrium Compositions Thermodynamic Properties and Performance Characteristics of Propellant Systems written by and published by . This book was released on 1979 with total page 103 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report summarized the methods and equations used in a Naval Weapons Center computer program called the NWC thermochemical program or the propellant evaluation program (PEP). The program is used to calculate high- temperature thermodynamic properties and performance characteristics of propellant systems, and it will handle a maximum of 12 chemical elements and 200 combustion products. Some of the parameters that can be computed with this program are flame temperature, chemical composition, enthalpy, entropy, specific heat ratio and molecular weight of both the combustion chamber and exhaust, frozen and shifting equilibrium, specific impulse, boost velocities, thrust coefficient, characteristic velocity, and exhaust gas velocity. The assumptions made, the limitations imposed, and the input data required for the solution of a specific problem by use of this program are discussed in detail. The appendices provide a working guide for those using the program and give examples of computer inputs. (Author).
Download or read book Thermodynamic Calculations for Rocket Engines written by Boris Aleksandrovich Nikolaev and published by . This book was released on 1962 with total page 222 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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. E amples 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. (Author).
Download or read book Chemical Rockets written by Subramaniam Krishnan and published by Springer Nature. This book was released on 2019-10-10 with total page 538 pages. Available in PDF, EPUB and Kindle. Book excerpt: The purpose of this book is to discuss, at the graduate level, the methods of performance prediction for chemical rocket propulsion. A pedagogical presentation of such methods has been unavailable thus far and this text, based upon lectures, fills this gap. The first part contains the energy-minimization to calculate the propellant-combustion composition and the subsequent computation of rocket performance. While incremental analysis is for high performance solid motors, equilibrium-pressure analysis is for low performance ones. Both are detailed in the book's second part for the prediction of ignition and tail-off transients, and equilibrium operation. Computer codes, adopting the incremental analysis along with erosive burning effect, are included. The material is encouraged to be used and presented at lectures. Senior undergraduate and graduate students in universities, as well as practicing engineers and scientists in rocket industries, form the readership.
Download or read book Thermofluiddynamics of Optimized Rocket Propulsions written by STRAUB and published by Birkhäuser. This book was released on 2012-12-06 with total page 267 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study has two declared aims: it presents the theoretical basis for a provably ideal comparative process for relaxing flows (ICP) and jus tifies its application to jet and, in particular, rocket engines. This will be treated in two parts. Part I offers a status quo report on current calculation methods, and compiles and explains briefly the most important data on selected pro minent rocket engines. Starting from the phenomenology of the dynamical and physico-chemical conversion processes in the fuel-oxidizer fluid mixture and in the burned gases, the ideal thermodynamic comparative process is then derived - as a defined sequential change of states in the system. In order to render this comparative process readily under standable, it is first applied to an appropriate model gas using alge braic equations for all relevant parameters. This model gas undergoes energy conversion processes without forfeiting the simplicity of pre sentation typical of classical gas dynamics. Above all, examination of this model offers proof that it is generally impermissible to use, as is done in practice, the familiar isentropic equation for flow changes of state continuously propagated in flow tube theory. Elementary calculations immediately indicate essential attributes which are also typical for relaxing, multicomponent, one-phase systems, such as the significant 'pressure drop phenomenon' or the establishment of the steady mass flow rate as an 'eigenvalue' of the comparative pro cess. Their relevance to the RE theory is stressed.
Download or read book Rocket Propellants written by Defense Documentation Center (U.S.) and published by . This book was released on 1960 with total page 176 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Analytical Investigation of Three General Methods of Calculating Chemical equilibrium Compositions written by Frank J. Zeleznik and published by . This book was released on 1960 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Publications of the Jet Propulsion Laboratory written by and published by . This book was released on 1962 with total page 350 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Kinetics Equilibria and Performance of High Temperature Systems written by Combustion Institute (U.S.). Western States Section and published by . This book was released on 1959 with total page 276 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A General Method for Calculating the Specific Impulse of High Energy Propellant Mixtures written by CARLOS M. BOWMAN and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: Methods are described for calculating specific impulses of propellant mixtures. The capacity of the computer (Burroughs 220) and the availability of thermodynamic data place practical restrictions on what systems can be calculated. The calculations center around the method of White, Johnson, and Dantzig for determining the equilibrium compositions of complex mixtures. By developing and applying matrix equations which describe both the thermodynamic data and the physical equations, the programming effort was reduced. Required input data to the program are the composition of the reaction mixture, the chamber and exit pressures, and a rough estimate of the chamber temperature. All other pertinent data are retrieved from magnetic tape by the computer program. A large number of problems may be solved without manual intervention. In addition to the specific impulse, the program calculates the characteristic velocity, the chamber and exit temperatures, compositions, enthalpies and entropies. (Author).
Download or read book Calculation of the Specific Impulse of Rocket Propellants written by Rudolph Edse and published by . This book was released on 1948 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
