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  • Other Sources  (16)
  • FLUID MECHANICS AND HEAT TRANSFER  (10)
  • SPACE TRANSPORTATION  (6)
  • 1
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    A mathematically simple turbulence closure model for attached and separated turbulent boundary layers (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal (ISSN 0001-1452); 23; 1684-169
    Format: text
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  • 2
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    Critical soft landing technology issues for future US space missions (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A programmatic need for research and development to support parachute-based landing systems has not existed since the end of the Apollo missions in the mid-1970s. Now, a number of planned space programs require advanced landing capabilities for which the experience and technology base does not currently exist. New requirements for landing on land with controllable, gliding decelerators and for more effective impact attenuation devices justify a renewal of the landing technology development effort that existed during the Mercury, Gemini, and Apollo programs. A study was performed to evaluate the current and projected national capability in landing systems and to identify critical deficiencies in the technology base required to support the Assured Crew Return Vehicle and the Two-Way Manned Transportation System. A technology development program covering eight landing system performance issues is recommended.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-185673 , NAS 1.26:185673
    Format: application/pdf
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  • 3
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    Transonic separated flow predictions based on a mathematically simple, nonequilibrium turbulence closure model (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A mathematically simple, turbulence closure model designed to treat transonic airfoil flows even with massive separation is described. Numerical solutions of the Reynolds-averaged, Navier-Stokes equations obtained with this closure model are shown to agree well with experiments over a broad range of test conditions.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-86826 , NAS 1.15:86826
    Format: application/pdf
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  • 4
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    Space Shuttle Orbiter - Leading edge structural design/analysis and material allowables (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Reinforced Carbon-Carbon (RCC), a structural composite whose development was targeted for the high temperature reentry environments of reusable space vehicles, has successfully demonstrated that capability on the Space Shuttle Orbiter. Unique mechanical properties, particularly at elevated temperatures up to 3000 F, make this material ideally suited for the 'hot' regions of multimission space vehicles. Design allowable characterization testing, full-scale development and qualification testing, and structural analysis techniques will be presented herein that briefly chart the history of the RCC material from infancy to eventual multimission certification for the Orbiter. Included are discussions pertaining to the development of the design allowable data base, manipulation of the test data into usable forms, and the analytical verification process.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 86-0949
    Format: text
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  • 5
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    Summary of all cycle II.5 shear and boundary layer measurements, aerodynamics (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The two measurement systems were used to measure mean velocity and velocity, mass flux, and total temperature fluctuations in the turbulent boundary on the fuselage of a KC-135 aircraft. The boundary layer thickness ranged between about 20 and 30 cm for the range of flight Mach numbers from about 0.25 to 0.85 and Reynolds numbers between 3 and 6 x 10 to the 6th power/m. The adaptation of each system for use in airborne applications is discussed. The data obtained from each system are given and compared with each other and they indicate that the two systems represent viable ones for use in future airborne turbulence experiments.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Proc. of the Aero-Optics Symp. on Electromagnetic Wave Propagation from Aircraft; p 459-464
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  • 6
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    Unsteady density and velocity measurements in the 6 foot x 6 foot wind tunnel (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The methods used and the results obtained in four aero-optic tests are summarized. It is concluded that the rather large values of density fluctuation appear to be the result of much higher Mach number than freestream and the violent turbulence in the flow as it separates from the turret. A representative comparison of fairing on-fairing off rms density fluctuation indicates essentially no effect at M = 0.62 and a small effect at M = 0.95. These data indicate that some slight improvement in optical quality can be expected with the addition of a fairing, although at M = 0.62 its effect would be nil. Fairings are very useful in controlling pressure loads on turrets, but will not have first order effects on optical quality. Scale sizes increase dramatically with increasing azimuth angle for a reprensentative condition. Since both scale sizes and fluctuation levels increase (total turbulence path length also increases) with azimuth angle, substantial optical degradation might be expected. For shorter wave lengths, large degradations occur.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Proc. of the Aero-Optics Symp. on Electromagnetic Wave Propagation from Aircraft; p 153-181
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  • 7
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    Space shuttle orbiter leading-edge flight performance compared to design goals (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Thermo-structural performance of the Space Shuttle orbiter Columbia's leading-edge structural subsystem for the first five (5) flights is compared with the design goals. Lessons learned from thse initial flights of the first reusable manned spacecraft are discussed in order to assess design maturity, deficiencies, and modifications required to rectify the design deficiencies. Flight data and post-flight inspections support the conclusion that the leading-edge structural subsystem hardware performance was outstanding for the initial five (5) flights.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Pt. 2; p 1065-1082
    Format: application/pdf
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  • 8
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    Atmospheric environment for space shuttle (STS-26) launch (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A summary of selected atmospheric conditions observed near Space Shuttle STS-26 launch time on September 29, 1988, at Kennedy Space Center, Florida is given. Values of ambient pressure, temperature, moisture, ground winds, visual observations (cloud), and winds aloft are included. The sequence of pre-launch Jimsphere measured vertical wind profiles is given. The final atmospheric tape, which consists of wind and thermodynamic parameters versus altitude, for STS-26 vehicle ascent has been constructed. The STS-26 ascent atmospheric data tape has been constructed by Marshall Space Flight Center's Earth Science and Applications Division to provide an internally consistent data set for use in post-flight performance assessments.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-100359 , NAS 1.15:100359
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  • 9
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    A generalized expression for lag-time in the gas-phase permeation of hollow tubes (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A generalized expression for the nonsteady-state parameter, lag-time, has been obtained from Fick's second law for gas-phase transport through hollow, cylindrical membranes. This generalized expression is simplified for three limiting cases of practical interest: (1) diffusion controlled transport, (2) phase boundary reaction control at the inlet surface, and (3) phase boundary reaction control at the outlet surface. In all three cases the lag-time expressions were found to be inversely proportional only to the diffusion coefficient and functionally dependent on the membrane radii. Finally, the lag-time expressions were applied to experimentally obtained lag-time data for alpha-phase titanium and alpha-phase iron.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Metallurgical Transactions A - Physical Metallurgy and Materials Science; 6A; Feb. 197
    Format: text
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  • 10
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    A laser Doppler velocimeter approach for near-wall three-dimensional turbulence measurements (1990)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A near-wall laser Doppler velocimeter approach is described that relies on a beam-turning probe which makes possible the direct measurement of the crossflow velocity at a grazing incident and the placement of optical components close to the flow region of interest regardless of test facility size. Other important elements of the approach are the use of digital frequency processing, an optically smooth measurement surface, and observation of the sensing volume at 90 degrees. The combination was found to dramatically reduce noise-in-signal effects caused by surface light scattering. Turbulent boundary-layer data to within 20 microns (y(sup+) approximately equal to 1) of the surface are presented which illustrate the potential of the approach.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-102841 , A-90207 , NAS 1.15:102841 , International Symposium on Application of Laser Techniques in Fluid Mechanics; Jul 09, 1990 - Jul 12, 1990; Lisbon; Portugal
    Format: application/pdf
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