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  • Other Sources  (2,261)
  • Fluid Mechanics and Thermodynamics  (1,208)
  • Spacecraft Propulsion and Power  (1,025)
  • AERODYNAMICS
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  • 2000-2004  (2,212)
  • 1940-1944  (49)
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  • Other Sources  (2,261)
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  • 1
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    Minnowbrook III: 2000 Workshop on Boundary Layer Transition and Unsteady Aspects of Turbomachinery Flows (2002)
    In:  CASI
    Details
    Publication Date: 2019-08-31
    Description: This volume and its accompanying CD-ROM contain materials presented at the Minnowbrook III-2000 Workshop on Boundary Layer Transition and Unsteady Aspects of Turbomachinery Flows held at the Syracuse University Minnowbrook Conference Center, Blue Mountain Lake, New York, August 20-23, 2000. Workshop organizers were John E. LaGraff (Syracuse University), Terry V Jones (Oxford University), and J. Paul Gostelow (University of Leicester). The workshop followed the theme, venue, and informal format of two earlier workshops: Minnowbrook I (1993) and Minnowbrook II (1997). The workshop was focused on physical understanding the late stage (final breakdown) boundary layer transition, separation, and effects of unsteady wakes with the specific goal of contributing to engineering application of improving design codes for turbomachinery. The workshop participants included academic researchers from the USA and abroad, and representatives from the gas-turbine industry and government laboratories. The physical mechanisms discussed included turbulence disturbance environment in turbomachinery, flow instabilities, bypass and natural transition, turbulent spots and calmed regions, wake interactions with attached and separated boundary layers, turbulence and transition modeling and CFD, and DNS. This volume contains abstracts and copies of the viewgraphs presented, organized according to the workshop sessions. The viewgraphs are included on the CD-ROM only. The workshop summary and the plenary-discussion transcripts clearly highlight the need for continued vigorous research in the technologically important area of transition, separated and unsteady flows in turbomachines.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA/CP-2001-210888 , E-12764 , NAS 1.55:210888 , NONP-NASA-CD-2002101352 , Minnowbrook III; Aug 20, 2000 - Aug 23, 2000; Blue Mountain Lake, NY; United States
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  • 2
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    Space Commercial Opportunities for Fluid Physics and Transport Phenomena Applications (2000)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: Microgravity research at NASA has been an undertaking that has included both science and commercial approaches since the late 80s and early 90s. The Fluid Physics and Transport Phenomena community has been developed, through NASA's science grants, into a valuable base of expertise in microgravity science. This was achieved through both ground and flight scientific research. Commercial microgravity research has been primarily promoted thorough NASA sponsored Centers for Space Commercialization which develop cost sharing partnerships with industry. As an example, the Center for Advanced Microgravity Materials Processing (CAMMP)at Northeastern University has been working with cost sharing industry partners in developing Zeolites and zeo-type materials as an efficient storage medium for hydrogen fuel. Greater commercial interest is emerging. The U.S. Congress has passed the Commercial Space Act of 1998 to encourage the development of a commercial space industry in the United States. The Act has provisions for the commercialization of the International Space Station (ISS). Increased efforts have been made by NASA to enable industrial ventures on-board the ISS. A Web site has been established at http://commercial/nasa/gov which includes two important special announcements. One is an open request for entrepreneurial offers related to the commercial development and use of the ISS. The second is a price structure and schedule for U.S. resources and accommodations. The purpose of the presentation is to make the Fluid Physics and Transport Phenomena community, which understands the importance of microgravity experimentation, aware of important aspects of ISS commercial development. It is a desire that this awareness will be translated into a recognition of Fluid Physics and Transport Phenomena application opportunities coordinated through the broad contacts of this community with industry.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Proceedings of the Fifth Microgravity Fluid Physics and Transport Phenomena Conference; 1972
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  • 3
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    Heat pipe systems using new working fluids (2004)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The performance of a heat pipe system is greatly improved by the use of a dilute aqueous solution of about 0.0005 and about 0.005 moles per liter of a long chain alcohol as the working fluid. The surface tension-temperature gradient of the long-chain alcohol solutions turns positive as the temperature exceeds a certain value, for example about 40.degree. C. for n-heptanol solutions. Consequently, the Marangoni effect does not impede, but rather aids in bubble departure from the heating surface. Thus, the bubble size at departure is substantially reduced at higher frequencies and, therefore, increases the boiling limit of heat pipes. This feature is useful in microgravity conditions. In addition to microgravity applications, the heat pipe system may be used for commercial, residential and vehicular air conditioning systems, micro heat pipes for electronic devices, refrigeration and heat exchangers, and chemistry and cryogenics.
    Keywords: Fluid Mechanics and Thermodynamics
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  • 4
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    Taming Liquid Hydrogen: The Centaur Upper Stage Rocket, 1958-2002 (2004)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: During its maiden voyage in May 1962, a Centaur upper stage rocket, mated to an Atlas booster, exploded 54 seconds after launch, engulfing the rocket in a huge fireball. Investigation revealed that Centaur's light, stainless-steel tank had split open, spilling its liquid-hydrogen fuel down its sides, where the flame of the rocket exhaust immediately ignited it. Coming less than a year after President Kennedy had made landing human beings on the Moon a national priority, the loss of Centaur was regarded as a serious setback for the National Aeronautics and Space Administration (NASA). During the failure investigation, Homer Newell, Director of Space Sciences, ruefully declared: "Taming liquid hydrogen to the point where expensive operational space missions can be committed to it has turned out to be more difficult than anyone supposed at the outset." After this failure, Centaur critics, led by Wernher von Braun, mounted a campaign to cancel the program. In addition to the unknowns associated with liquid hydrogen, he objected to the unusual design of Centaur. Like the Atlas rocket, Centaur depended on pressure to keep its paper-thin, stainless-steel shell from collapsing. It was literally inflated with its propellants like a football or balloon and needed no internal structure to give it added strength and stability. The so-called "pressure-stabilized structure" of Centaur, coupled with the light weight of its high- energy cryogenic propellants, made Centaur lighter and more powerful than upper stages that used conventional fuel. But, the critics argued, it would never become the reliable rocket that the United States needed.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/SP-2004-4230 , LC-2004-042092
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  • 5
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    Fabrication process for combustion chamber/nozzle assembly (2001)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: An integral, lightweight combustion chamber/nozzle assembly for a rocket engine has a refractory metal shell defining a chamber of generally frusto-conical contour. The shell communicates at its smaller end with a rocket body, and terminates at its larger end in a generally contact contour, which is open at its terminus and which serves as a nozzle for the rocket engine. The entire inner surface of the refractory metal shell has a thermal and oxidation barrier layer applied thereto. An ablative silica phenolic insert is bonded to the exposed surface of the thermal and oxidation barrier layer. The ablative phenolic insert provides a chosen inner contour for the combustion chamber and has a taper toward the open terminus of the nozzle. A process for fabricating the integral, lightweight combustion chamber/nozzle assembly is simple and efficient, and results in economy in respect of both resources and time.
    Keywords: Spacecraft Propulsion and Power
    Format: application/pdf
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  • 6
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    Injector for liquid fueled rocket engine (2000)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: An injector for liquid fueled rocket engines wherein a generally flat core having a frustoconical dome attached to one side of the core to serve as a manifold for a first liquid, with the core having a generally circular configuration having an axis. The other side of the core has a plurality of concentric annular first slots and a plurality of annular concentric second slots alternating with the first slots, the second slots having a greater depth than said first slots. A bore extends through the core for inletting a second liquid into said core, the bore intersecting the second slots to feed the second liquid into the second slots. The core also has a plurality of first passageways leading from the manifold to the first annular slots for feeding the first liquid into said first slots. A faceplate brazed to said other side of the core is provided with apertures extending from the first and second slots through said face plate, these apertures being positioned to direct fuel and liquid oxygen into contact with each other in the combustion chamber. The first liquid may be liquid oxygen and the second liquid may be kerosene or liquid hydrogen.
    Keywords: Spacecraft Propulsion and Power
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  • 7
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    Physical Sciences Research Priorities and Plans in OBPR (2002)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: This paper presents viewgraphs of physical sciences research priorities and plans at the Office of Biological and Physical Sciences Research (OBPR). The topics include: 1) Sixth Microgravity Fluid Physics and Transport Phenomena Conference; 2) Beneficial Characteristics of the Space Environment; 3) Windows of Opportunity for Research Derived from Microgravity; 4) Physical Sciences Research Program; 5) Fundamental Research: Space-based Results and Ground-based Applications; 6) Nonlinear Oscillations; and 7) Fundamental Research: Applications to Mission-Oriented Research.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Sixth Microgravity Fluid Physics and Transport Phenomena Conference; 1; 1-11; NASA/CP-2002-211212/VOL1
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  • 8
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    In-Space Propulsion Program Overview and Status (2003)
    In:  Other Sources
    Details
    Publication Date: 2019-08-27
    Description: NASA's In-Space Propulsion (ISP) Program is designed to develop advanced propulsion technologies that can enable or greatly enhance near and mid-term NASA science missions by significantly reducing cost, mass, and/or travel times. These technologies include: Solar Electric Propulsion, Aerocapture, Solar Sails, Momentum Exchange Tethers, Plasma Sails and other technologies such as Advanced Chemical Propulsion. The ISP Program intends to develop cost-effective propulsion technologies that will provide a broad spectrum of mission possibilities, enabling NASA to send vehicles on longer, more useful voyages and in many cases to destinations that were previously unreachable using conventional means. The ISP approach to identifying and prioritizing these most promising technologies is to use mission and system analysis and subsequent peer review. The ISP program seeks to develop technologies under consideration to Technology Readiness Level (TRL) -6 for incorporation into mission planning within 3-5 years of initiation. The NASA TRL 6 represents a level where a technology is ready for system level demonstration in a relevant environment, usually a space environment. In addition, maximum use of open competition is encouraged to seek optimum solutions under ISP. Several NASA Research Announcements (NRA's) have been released asking industry, academia and other organizations to propose propulsion technologies designed to improve our ability to conduct scientific study of the outer planets and beyond. The ISP Program is managed by NASA Headquarters Office of Space Science and implemented by the Marshall Space Flight Center in Huntsville, Alabama.
    Keywords: Spacecraft Propulsion and Power
    Type: International Electric Propulsion Conference 2003; Mar 17, 2003 - Mar 21, 2003; Toulouse; France
    Format: text
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  • 9
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    NASA Research Announcement (2002)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: This paper presents viewgraphs of NASA's strategic and fundamental research program at the Office of Biological and Physical Research (OBPR). The topics include: 1) Colloid-Polymer Samples; 2) Pool Boiling Experiment; 3) The Dynamics of Miscible Interfaces: A Space Flight Experiment (MIDAS); and 4) ISS and Ground-based Facilities.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Sixth Microgravity Fluid Physics and Transport Phenomena Conference; 1; 12-23; NASA/CP-2002-211212/VOL1
    Format: text
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  • 10
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    Microgravity Sciences Program Overview (2000)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: This overview presents in viewgraph form, the NASA Program organization regarding fluid physics, physical sciences research in space and the connection to biology, the dual thrust of the fluid physics program, and the immediate and future plans of the physical science research division.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Proceedings of the Fifth Microgravity Fluid Physics and Transport Phenomena Conference; 4-17
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