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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Airloads investigation of an 0.30-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 5
Pressure data are presented in tabular form on the lower wing surface of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 6
Pressure data are presented in tabular form on the upper wing surface of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Airloads investigation of an 0.030 scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 7
Pressure data are presented in tabular form on the left and right vertical tail surface of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the arc 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 8
Pressure data are presented in tabular form on the SRM booster of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 9
Pressure data are presented in tabular form on the external tank and the SRM nozzle of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Airloads investigation of an 0.030-scale model of the Space Shuttle Vehicle 140 A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for MACH range 0.6 to 1.4 (IA14A), volume 10
Pressure data are presented in tabular form on the external tank base and SRM booster base of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 11
Pressure data are presented in tabular form on the external tank attach points and the external tank base rake of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Data correlation and analysis of arc tunnel and wind tunnel tests of RSI joints and gaps, phase 2. Volume 1: Technical report
Heat transfer data measured in gaps representative of those being employed for joints in the space shuttle reusable surface insulation (RSI) thermal protection systems (TPS) were assimilated, analyzed, and correlated. Several types of gap were investigated with emphasis on simple butt joints. Gap widths ranged from 0.0 to 0.76 cm and depths ranged from 1 to 6 cm. Laminar, transitional, and turbulent boundary layer flows over the gap opening were investigated. The angle between gap axis and external flow was varied between 0 and pi/2 radians. The contoured cross section gap performed significantly better than all other wide gaps and slightly better than all other narrow gap geometries. Three dimensional heating variations were observed within gaps in the absence of external flow pressure gradients. Interactions between heating within gaps and heating of adjacent top tile surfaces were observed. Gaps aligned with the flow were observed to promote boundary layer transition. Heat transfer correlation equations were obtained for many of the tests. The TPS thickness requirements with and without gaps were computed for a current shuttle entry trajectory. Experimental data employed in the study are summarized. A description of each test facility, run schedule and test conditions, model descriptive information, and heat flux data are included.
Data correlation and analysis of arc tunnel and wind tunnel tests of RSI joints and gaps, phase 2. Volume 2: Data report, part 1
For abstract, see N75-28103.
Data correlation and analysis of arc tunnel and wind tunnel tests of RSI joints and gaps, phase 2. Volume 2: Data report, part 2
For abstract, see N75-28103.
Plasma clouds and auroral arcs
Correlation techniques for magnetospheric observations of various types by instrumented spacecraft in synchronous orbit are discussed. Emphasis is placed on ideas for possible use in studies with GEOS satellite during the International Magnetospheric Study, and comparison of auroral and magnetospheric plasma features are considered. Correlation between ATS-5 particle detector measurements with ground based measurement and other spacecraft such as Explorer 45 is described. Observations from ATS-6 instrument are briefly mentioned.
Transonic flow about a thick circular-arc airfoil
An experimental and theoretical study of transonic flow over a thick airfoil, prompted by a need for adequately documented experiments that could provide rigorous verification of viscous flow simulation computer codes, is reported. Special attention is given to the shock-induced separation phenomenon in the turbulent regime. Measurements presented include surface pressures, streamline and flow separation patterns, and shadowgraphs. For a limited range of free-stream Mach numbers the airfoil flow field is found to be unsteady. Dynamic pressure measurements and high-speed shadowgraph movies were taken to investigate this phenomenon. Comparisons of experimentally determined and numerically simulated steady flows using a new viscous-turbulent code are also included. The comparisons show the importance of including an accurate turbulence model. When the shock-boundary layer interaction is weak the turbulence model employed appears adequate, but when the interaction is strong, and extensive regions of separation are present, the model is inadequate and needs further development.
Rocket-based magnetic observations of auroral Birkeland currents in association with a structured auroral arc
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Mars gravity field based on a short-arc technique
The magnitudes of 92 surface mass points at designated locations were estimated from the radio tracking data of the Mariner Mars 1971 (M9) orbiter. This result is the first mass point model of a global field. The derived surface mass distribution correlates positively with the visible topography. The Hellas basin contains a mass deficiency, in contrast to some of the lunar basins which contain mass excesses. The Mars gravity field represented by the four parameters of an optimally located mass point (superimposed on an oblate spheroid) has third- and fourth-degree harmonics comparable to those of the complete model.
Variable radio source structure on a scale of several minutes of arc
Results are reported for high-frequency (0.75, 1.40, 3.24, 6.63, and 10.63 GHz) flux-density measurements of about 100 radio sources exhibiting low-frequency cutoffs. At least three sources (4C 79.4, 4C 79.15, and PKS 2344+09) showed variable structure on a scale ranging from a fraction of an arcmin to as much as 15 arcmin which appears to change significantly on a time scale of several months. The visual fields of these sources and their companion components are searched for identifiable objects, and complete radio spectra as well as contour maps are presented for some of the sources. It is suggested that the variable structure may result from the existence of several emission centers that are highly variable in flux density but fixed in position.
Development of a dispersion strengthened nickel base alloy using the high intensity arc process
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