A survey of techniques for recognizing parallel processable streams in computer programs
Survey of techniques for recognizing parallel processable streams in computer programs
Gonzalez, M. J.↗
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Parallel gap welding Kovar ribbons to copper conductor printed wiring boards
Parallel gap welding Kovar ribbons to copper conductor printed wiring boards
Mc Daniel, G. E.↗
Parallel implementation of a single assignment language
High level computer programming language /SAMPLE/ and parallel processing system to implement it
Chamberlin, D. D.↗
Metal structures with parallel pores of uniform size
Description of techniques for preparing metallic structures with parallel, uniformly sized pores
Sherfy, J.↗
Space shuttle: Determination of the static stability characteristics of the 0.00285-scale MDAC parallel burn launch configuration
Aerodynamic force and moment coefficient data for parallel burn vehicle launch configurations tested in trisonic wind tunnel for static stability
Blackwell, K. L.↗
Safety analysis of parallel versus series propellant loading of the space shuttle. Volume 2: Technical discussion
Safety and hazards analysis of parallel versus series loading of space shuttle using liquid hydrogen and liquid oxygen propellants - technical discussion
Hamberg, O.↗
Safety analysis of parallel versus series propellant loading of the space shuttle Volume 1: Management summary report
Safety analysis of parallel versus series propellant loading of space shuttle
Wolfe, R. R.↗
A survey of techniques for recognizing parallel processable streams in computer programs
Computer programs parallel processable tasks recognition techniques survey, discussing algorithms
Gonzalez, M. J.↗
The mixing of two parallel streams of dissimilar fluids. I - Analytical development
Laminar and turbulent mixing of two parallel streams of dissimilar fluids, using similarity transformation
Baker, R. L.↗
Turbulent mixing of two parallel streams - An experimental investigation
Turbulent mixing of two parallel similar and dissimilar fluid streams, comparing velocity and density profiles measurements with similarity solution
Baker, R. L.↗
Energy deposition in parallel-plate plasma accelerators
Parallel plate plasma accelerator energy deposition, considering kinetic and thermal modes based on flow velocity, temperature and Mach number measurements
Di Capua, M. S.↗
The effect of stable thermal stratification on the stability of viscous parallel flows
Stability theory for thermal stratified viscous parallel flows at Prandtl number of unity, considering atmospheric boundary layer and jet stream mechanisms
Gage, K. S.↗
Turbulent flow between parallel plates with gas property variation
Numerical solution of coupled boundary layer equations describing strongly cooled turbulent flow of gas between parallel plates with property variation
Mceligot, D. M.↗
Redundancy verification of parallel systems as related to element MTBF and acceptance risk of system failure
Redundancy verification of parallel systems related to element MTBF and decision maker perspective involving acceptance risk of system failure
Moreno, F. J.↗
Parallel-plate viscometer
Viscometer consists of movable vertical rod with one optical flat fixed to its lower end and centered over second optical flat held rigidly parallel to moveable flat. Two perforated diaphragms of thin metal permit limited amount of vertical movement of rod carrying movable flat, but resist lateral movement.
Fearnehough, H. T.↗
Stage separation of parallel-staged shuttle vehicles, a capability assessment
The separation concept for stage separation of parallel staged space shuttle vehicles is discussed. The forward link separation concept is emphasized. The effects of aerodynamic interference and component mass are analyzed. Qualitative measurements used to perform a preliminary evaluation of various separation system concepts are presented. Line drawings are included to clarify the mechanisms and spacecraft structures used in stage separation.
Hurley, M. J.↗
Aerodynamic stability and drag characteristics of a parallel burn/SRM ascent configuration at Mach numbers from 0.6 to 4.96
Experimental aerodynamic investigations were conducted in the NASA/MSFC 14-inch trisonic wind tunnel during March 1972 on a .003366 scale model of a solid rocket motor version of the space shuttle ascent configuration. The configuration consisted of a parallel burn solid rocket motor booster on an external H-O centerline tank orbiter. Six component aerodynamic force and moment date were recorded over an angle of attack range from -10 to 10 deg at zero degrees sideslip and over a sideslip range from -10 to 10 deg at 0, +6, and -6 deg angle of attack. Mach number ranged from 0.6 to 4.96. The performance and stability characteristics of the complete ascent configuration and build-up, and the effects of variations in tank diameter, orbiter incidence, fairings and positioning of the solid rocket motors and tank fins were determined.
Sims, J. F.↗
Aerodynamic stability and drag characteristics of a parallel burn/SRM ascent configuration (M equals 0.6 to 4.96)
Experimental aerodynamic investigations were conducted in the NASA/MSFC 14-inch trisonic wind tunnel during April 1972 on a 0.004-scale model of a solid rocket motor version of the space shuttle ascent configuration. The configuration consisted of a parallel burn solid rocket motor booster on an external HO centerline tank orbiter. Six component aerodynamic force and moment data were recorded over an angle of attack range from -10 deg to +10 deg at zero degrees sideslip and over a sideslip range from -10 deg to +10 deg at zero degrees angle of attack. Mach numbers ranged from 0.6 to 4.96. The purpose of the test was to determine the performance and stability characteristics of the complete ascent configuration and buildup, and to determine the effects of variations in HO tank and SRM nose shaping, orbiter incidence and position, and position of the solid rocket motors.
Sims, F.↗