Add to ORKGThe FORTRAN IV Program developed to analyze the flow field associated with scramjet exhaust systems is presented. The instructions for preparing input and interpreting output are described. The program analyzes steady three dimensional supersonic flow by the reference plane characteristic technique. The governing equations and numerical techniques employed are presented in Volume 1 of this report
The use of a computer code for the calculation of two dimensional inlet flow fields in a supersonic ...
Computer programs to calculate the incompressible potential flow, corrected for compressibility, in ...
The computer program documentation for the design and analysis of supersonic configurations is prese...
A second order numerical method employing reference plane characteristics has been developed for the...
A computer program for analyzing the nozzle for a hypersonic scramjet by a second order characterist...
This report summarizes work accomplished under Contract No. NAS1-12726 towards the development of co...
Numerical codes developed for the calculation of three-dimensional nozzle exhaust flow fields associ...
A comprehensive computational fluid dynamics effort was conducted from 1987 to 1990 to properly desi...
The factors which influence the design and selection of a nozzle for a hypersonic scramjet are descr...
The reference-plane method of characteristics is applied to the computation of the supersonic flow i...
A numerical procedure permitting the rapid determination of the internal performance of a class of s...
FORTRAN 4 program for computerized design of two dimensional supersonic nozzles with sharp edged thr...
A FORTRAN IV program for analyzing the nozzle flow for a hypersonic scramjet by a two dimensional se...
A computer program previously developed to analyze three-dimensional supersonic nozzles by the metho...
A computer implemented numerical method for predicting the flow in and about an isolated three dimen...
The use of a computer code for the calculation of two dimensional inlet flow fields in a supersonic ...
Computer programs to calculate the incompressible potential flow, corrected for compressibility, in ...
The computer program documentation for the design and analysis of supersonic configurations is prese...
A second order numerical method employing reference plane characteristics has been developed for the...
A computer program for analyzing the nozzle for a hypersonic scramjet by a second order characterist...
This report summarizes work accomplished under Contract No. NAS1-12726 towards the development of co...
Numerical codes developed for the calculation of three-dimensional nozzle exhaust flow fields associ...
A comprehensive computational fluid dynamics effort was conducted from 1987 to 1990 to properly desi...
The factors which influence the design and selection of a nozzle for a hypersonic scramjet are descr...
The reference-plane method of characteristics is applied to the computation of the supersonic flow i...
A numerical procedure permitting the rapid determination of the internal performance of a class of s...
FORTRAN 4 program for computerized design of two dimensional supersonic nozzles with sharp edged thr...
A FORTRAN IV program for analyzing the nozzle flow for a hypersonic scramjet by a two dimensional se...
A computer program previously developed to analyze three-dimensional supersonic nozzles by the metho...
A computer implemented numerical method for predicting the flow in and about an isolated three dimen...
The use of a computer code for the calculation of two dimensional inlet flow fields in a supersonic ...
Computer programs to calculate the incompressible potential flow, corrected for compressibility, in ...
The computer program documentation for the design and analysis of supersonic configurations is prese...