Accession Number : AD0479695
Title : TURBOFAN-RAMJET ENGINE STUDIES. VOLUME II - COMPUTATION PROGRAM - DATA.
Descriptive Note : Final rept.,
Corporate Author : NORD AVIATION CHATILLON-SOUS-BAGNEUX (FRANCE)
Personal Author(s) : Chaulin, P. ; Sandre, P.
Report Date : MAY 1964
Pagination or Media Count : 188
Abstract : The new IBM 650 computation program for studying the dimensions and performance of a combined turbofan-ramjet engine is described. Flow computations have used a specific heat ratio varying from engine inlet to exit. The theory of enthalpies has been used for computation of combustion in the combustion chamber, burned gas flow in the common exhaust nozzle, and fuel flow in the turbofan. This program enables calculations for the combined turbofan-ramjet, the pure turbofan, and pure ramjet engine. Geometric dimensions, except the fan exit cross-section area and the common exit nozzle throat, are given data. The exceptions, computed by the program, are variable during flight. These cross-sectional areas together with fuel flow permit the determination of the best operation of the engine for each flight case. In addition to the calculation assumptions and equation details, the other major blocks of data presented are: (1) manufacturers' documentation on characteristics of the three turbofans used in the study and (2) numerical values for the different parameters, coefficients, and functions used in the computation. (Author)
Descriptors : (*TURBORAMJET ENGINES, PERFORMANCE(ENGINEERING)), (*COMBUSTION, MATHEMATICAL ANALYSIS), TURBOFAN ENGINES, RAMJET ENGINES, ENGINE FUEL SYSTEMS COMPONENTS, SYSTEMS ENGINEERING, THERMODYNAMIC CYCLES, GEOMETRY, SPECIFIC HEAT, SECONDARY FLOW, NOZZLE GAS FLOW, COMBUSTION CHAMBER GASES, TURBOJET EXHAUST NOZZLES, TURBOJET INLETS, FUEL CONSUMPTION, COMPUTER PROGRAMMING, JET MIXING FLOW, COMPRESSOR ROTORS, COMBUSTION CHAMBERS.
Subject Categories : Fluid Mechanics
Combustion and Ignition
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE