NASA computer program aids American designers
The application of the NASTRAN program to solve civilian structural engineering problems is reported. Results and predicted results of the program's use are included.
Zylstra, D.↗
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An improved multiple linear regression and data analysis computer program package
NEWRAP, an improved version of a previous multiple linear regression program called RAPIER, CREDUC, and CRSPLT, allows for a complete regression analysis including cross plots of the independent and dependent variables, correlation coefficients, regression coefficients, analysis of variance tables, t-statistics and their probability levels, rejection of independent variables, plots of residuals against the independent and dependent variables, and a canonical reduction of quadratic response functions useful in optimum seeking experimentation. A major improvement over RAPIER is that all regression calculations are done in double precision arithmetic.
Sidik, S. M.↗
NASTRAN thermal analyzer: A general purpose finite element heat transfer computer program
The program not only can render temperature distributions in solids subjected to various thermal boundary conditions, including effects of diffuse-gray thermal radiation, but is fully compatible in capacity and in the finite-element model representation with that of its structural counterpart in the NASTRAN system. The development history of the finite-element approach for determining temperatures is summarized. The scope of analysis capability, program structure, features, and limitations are given with the objective of providing NASTRAN users with an overall veiw of the NASTRAN thermal analyzer.
Lee, H.↗
Calculation of radiation induced swelling of uranium mononitride using the digital computer program CYGRO 2
Fuel volume swelling and clad diametral creep strains were calculated for five fuel pins, clad with either T-111 (Ta-8W-2.4Hf) or PWC-11 (Nb-1Zr-0.1C). The fuel pins were irradiated to burnups between 2.7 and 4.6%. Clad temperatures were between 1750 and 2400 F (1228 and 1589 K). The maximum percentage difference between calculated and experimentally measured values of volumetric fuel swelling is 60%.
Davison, H. W.↗
Computer program for transient response of structural rings subjected to fragment impact
Mathematical optimization of containment/deflection system would save time, effort, and material as well as afford designer greater opportunity to investigate new ideas and variety of materials.
Wu, R. W.↗
Aerotherm charring materials ablation computer program
Ablating-surface boundary conditions involve considerations of surface thermochemistry. Several programs may be used to provide surface thermochemistry information.
Powars, C. A.↗
Ascent control analysis for S-II derivative launch vehicles, digital computer program
Model is used for analysis of the six degrees-of-freedom dynamics of general launch vehicle during atmospheric boost. Equations of motion are developed for rigid body and flat earth. Case may be started at any time beginning with ignition of stage and may be ended upon, or prior to, stage burnout. End of case may be at a specified time or based on propellant expended.
Andrews, P. D.↗
Computer program for calculation of thermodynamic and transport properties of complex chemical systems
Program performs calculations such as chemical equilibrium for assigned thermodynamic states, theoretical rocket performance for both equilibrium and frozen compositions during expansion, incident and reflected shock properties, and Chapman-Jouget detonation properties. Features include simplicity of input and storage of all thermodynamic and transport property data on master tape.
Svehla, R. A.↗
A computer program for calculating design and off-design performance for turbojet and turbofan engines
Program uses component performance maps to enable user to do analytical engine cycle calculations. Through scaling procedure, each of the component maps can be used to represent a family of maps. Either convergent or convergent-divergent nozzles may be used.
Koenig, R. W.↗
Computer program to determine the irrotational nozzle admittance
Irrotational nozzle admittance is the boundary condition that must be satisfied by combustor flow oscillations at nozzle entrance. Defined as the ratio of axial velocity perturbation to the pressure perturbation at nozzle entrance, nozzle admittance can also be used to determine whether wave motion in nozzle under consideration adds or removes energy from combustor oscillations.
Bell, W. A.↗
A computer program for calculating design and off-design performance of two- and three-spool turbofans with as many as three nozzles
Program uses component performance maps to enable user to do analytical engine cycle calculations. Either convergent or convergent-divergent nozzles may be used.
Fishbach, L. H.↗
Computer program for compressible flow network analysis
Program solves problem of an arbitrarily connected one dimensional compressible flow network with pumping in the channels and momentum balancing at flow junctions. Program includes pressure drop calculations for impingement flow and flow through pin fin arrangements, as currently found in many air cooled turbine bucket and vane cooling configurations.
Wilton, M. E.↗
Computer program calculates quasi-one-dimensional flow across face seals and narrow slots
Program calculates mass and volume leakage across seal; mean friction factor; force; center of pressure; and distributions of pressure, temperature, density, friction parameter, velocity, and Mach number across seal for both laminar flow and turbulent flow regimes and for choked and subsonic flow.
Zuk, J.↗
Computer program for the prediction of reorientation flow dynamics
Program uses Navier-Stokes and continuity equations for incompressible, viscous fluid as the basic equations governing reorientation flow dynamics. Program can simulate curved as well as straight-walled boundaries; has ability to calculate both free-surface and confined flows; and can be used in either cylindrical or plane geometry.
Betts, W. S., Jr.↗
DORCA 2 computer program. Volume 2: Programmer's manual
A guide for coding the Dynamic Operational Requirements and Cost Analysis Program (DORCA 2) is presented. The manual provides a detailed operation of every subroutine, the layout in core of the major matrices and arrays, and the meaning of all program values. Flow charts are included.
Gold, B. J.↗
Study 2.5 final report. DORCA computer program. Volume 5: Analysis report
A modification of the Dynamic Operational Requirements and Cost Analysis Program to perform traffic analyses of the automated satellite program is described. Inherent in the analyses of the automated satellite program was the assumption that a number of vehicles were available to perform any or all of the missions within the satellite program. The objective of the modification was to select a vehicle or group of vehicles for performing all of the missions at the lowest possible cost. A vehicle selection routine and the capability to simulate ground based vehicle operational modes were incorporated into the program.
Campbell, N.↗
A Limited Survey of General Purpose Finite Element Computer Programs
Ten representative programs are compared. A listing of additional programs encountered during the course of this effort is also included. Tables are presented to show the structural analysis, material, load, and modeling element capability for the ten selected programs.
Glaser, J. C.↗
Computer programs for the solution of systems of linear algebraic equations
FORTRAN subprograms for the solution of systems of linear algebraic equations are described, listed, and evaluated in this report. Procedures considered are direct solution, iteration, and matrix inversion. Both incore methods and those which utilize auxiliary data storage devices are considered. Some of the subroutines evaluated require the entire coefficient matrix to be in core, whereas others account for banding or sparceness of the system. General recommendations relative to equation solving are made, and on the basis of tests, specific subprograms are recommended.
Sequi, W. T.↗