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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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Investigations of the 0.020-scale 88-OTS Integrated Space Shuttle Vehicle Jet-Plume Model in the NASA/Ames Research Center 11 by 11-Foot Unitary Plan Wind Tunnel (IA80)
Tabulated force and pressure data are presented for the orbiter base and fuselage. For abstract, see N76-33263.
Investigations of the 0.020-scale 88-OTS Integrated Space Shuttle Vehicle Jet-Plume Model in the NASA/Ames Research Center 11 by 11-Foot Unitary Plan Wind Tunnel (IA80)
Tabulated pressure data are presented for the orbiter fuselage, the orbiter bodyflap upper surface, and the orbiter bodyflap lower surface. For abstract, see N76-33263.
Investigations of the 0.020-scale 88-OTS Integrated Space Shuttle Vehicle Jet-Plume Model in the NASA/Ames Research Center 11 by 11-Foot Unitary Plan Wind Tunnel (IA80)
Tabulated pressure data are presented for the external tank and the external tank base. For abstract, see N76-33263.
Use of LARS System for the quantitative determination of smoke plume lateral diffusion coefficients from ERTS images of Viginia
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JANNAF Handbook: Rocket Exhaust Plume Technology: Fluid Dynamic Flow Models - Chapter 2
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Modifications to once-through cooling water discharge structure to achieve entrainment mixing and lateral transport of thermal plume
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Aerial remote sensing of thermal plumes
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Important considerations in a simple numerical plume model
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A model for shore-attached thermal plumes in rivers
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Some practical aspects of thermal plume analysis
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Thermal plume evaluation program of Indian Point Nuclear Power Plant
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Patterns of thermal plume configuration: Implications for environmental impact assessment and resource management
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Ion beam plume and efflux characterization flight experiment study
A flight experiment and flight experiment package for a shuttle-borne flight test of an 8-cm mercury ion thruster was designed to obtain charged particle and neutral particle material transport data that cannot be obtained in conventional ground based laboratory testing facilities. By the use of both ground and space testing of ion thrusters, the flight worthiness of these ion thrusters, for other spacecraft applications, may be demonstrated. The flight experiment definition for the ion thruster initially defined a broadly ranging series of flight experiments and flight test sensors. From this larger test series and sensor list, an initial flight test configuration was selected with measurements in charged particle material transport, condensible neutral material transport, thruster internal erosion, ion beam neutralization, and ion thrust beam/space plasma electrical equilibration. These measurement areas may all be examined for a seven day shuttle sortie mission and for available test time in the 50 - 100 hour period.
Pretest information for a test to validate plume simulation procedures (FA-17)
The results of an effort to plan a final verification wind tunnel test to validate the recommended correlation parameters and application techniques were presented. The test planning effort was complete except for test site finalization and the associated coordination. Two suitable test sites were identified. Desired test conditions were shown. Subsequent sections of this report present the selected model and test site, instrumentation of this model, planned test operations, and some concluding remarks.
Nitric oxide production in the stratosphere within the Space Shuttle's solid rocket motor plumes
This study focuses on establishing the sensitivity of predictions of NO production to uncertainties in altitude, reaction rate coefficients, turbulent mixing rates, and Mach disk size and location. The results show that relatively large variations in parameters related to these phenomena had surprisingly little effect on predicted NO production.
Observations of the convective plume of a lake under cold-air advective conditions
Moderating effects of Lake Apopka, Florida, on downwind surface temperatures were evaluated under cold-air advective conditions. Point temperature measurements north and south of the lake and data obtained from a thermal scanner flown at 1.6 km indicate that surface temperatures directly downwind may be higher than surrounding surface temperatures by as much as 5 C under conditions of moderate winds (about 4 m/s). No substantial temperature effects were observed with surface wind speed less than 1 m/s. Fluxes of sensible and latent heat from Lake Apopka were calculated from measurements of lake temperature, net radiation, relative humidity, and air temperature above the lake. Bulk transfer coefficients and the Bowen ratio were calculated and found to be in agreement with reported data for nonadvective conditions.