ALBERT

All Library Books, journals and Electronic Records Telegrafenberg

X
feed icon rss

Your email was sent successfully. Check your inbox.

An error occurred while sending the email. Please try again.

Proceed reservation?

Export
  • 1
    facet.materialart.
    Unknown
    Open fissure mineralization at 2600 m depth in Long Valley Exploratory Well (California) - insight into the history of the hydrothermal system (2003)
    In:  Journal of Volcanology and Geothermal Research, pp. 347-363, vol. 127, no. 3-4
    Details
    Publication Date: 2003
    Keywords: CC 4 ; Coordinating Committee ; Continental Drilling ; ICDP
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY ILP
  • 2
    facet.materialart.
    Unknown
    Effects of the air traffic control system on the supersonic transport (1965)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Description: Supersonic transport time and fuel problems - relation to air traffic control system
    Keywords: NAVIGATION
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 3
    facet.materialart.
    Unknown
    Effect of angle of attack on boundary-layer transition at Mach 21 (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Slender cone boundary layer transition under angle of attack at Mach 21 with promoted leeward and fixed windward ray
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; YAL SOCIETY (
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 4
    facet.materialart.
    Unknown
    Fresh attack on laminar flow (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Laminar flow control is a technology with great potential for aircraft drag reduction. Stabilization of laminar boundary layers became known as natural laminar flow (NLF) and research led to the development of NLF airfoils. Research was also conducted on stabilization by suction, referred to as laminar flow control (LFC). Experiments demonstrated that extensive laminar flow could be achieved in flight. However, there remained doubts regarding the practicality of producing, with the technology then available, wing surfaces sufficiently smooth and wavefree to meet laminar-flow criteria and maintaining the wing surface quality in normal service. In 1976, the Aircraft Energy Efficiency (ACEE) program was begun by NASA to develop fuel-conservative technology for commercial transports. The progress of the ACEE program is discussed. Attention is given to LFC wing structures, and LFC leading-edge systems.
    Keywords: AERODYNAMICS
    Type: Aerospace America (ISSN 0740-722X); 22; 72-76
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 5
    facet.materialart.
    Unknown
    Hypersonic boundary-layer transition on ablating and nonablating cones (1969)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Ablation effects on transition Reynolds number of hypersonic boundary layer on slender cones
    Keywords: FLUID MECHANICS
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 6
    facet.materialart.
    Unknown
    Spreading of a turbulent disturbance. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The presented paper shows the effect of local Mach number on the turbulent disturbance spreading angle relative to the wall and on lateral disturbance spreading angles. Almost all the disturbances angles relative to the wall were determined from investigations where hot-wire contours or hot-film surveys of a 'laminar' boundary layer were obtained. Lateral disturbance spreading angles were obtained from investigations of various conditions including turbulent bursts, reported observations of transverse contamination, and observed transitional flow. It is noted that the disturbance spreading angle relative to the wall seems to remain essentially invariant with Mach number, while the lateral spreading angle decreases sharply with increasing Mach number up to about 6. The good agreement between lateral disturbance spreading angle data and data for the variation of turbulent jet spreading angle with Mach number implies that in the lateral dimension, turbulence in a boundary layer may develop essentially free of wall constraints (similar to a free shear layer).
    Keywords: FLUID MECHANICS
    Type: AIAA Journal; 10; July 197
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 7
    facet.materialart.
    Unknown
    Cone transitional boundary-layer structure at Me = 14. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Experimental results suggest that the boundary-layer mean profiles in hypersonic flows may be highly transitional in the outer part of the boundary layer before the transition process is detected at the surface. Means of determining the initial location where the transition process begins in the outer part of the boundary layer are considered.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; May 1972
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 8
    facet.materialart.
    Unknown
    Turbulent bursts and rings on a cone in helium at Me = 7.6. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Review of data obtained on turbulent burst geometry and growth characteristics for cone boundary-layer transition in a helium wind tunnel at a boundary-layer edge Mach number (Me) of 7.6. Detailed data concerning turbulent spot geometry and downstream propagation velocities were obtained using a spark schlieren system with sequential spark capability. In one particular test evidence of a symmetrical turbulent burst ring was obtained; all other bursts developed in a singular random manner. Profiles of the apparent outer edges of the bursts were obtained, and the velocities of the leading and trailing edges of the bursts relative to the local velocity were determined. The velocities of the leading and trailing edges were found to be fairly consistent for each observation, with the leading edge of the burst traveling at about local edge velocity, while the trailing edge moved supersonically relative to local speed.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Oct. 197
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 9
    facet.materialart.
    Unknown
    SST engages the air-traffic control system. (1966)
    In:  Other Sources
    Details
    Publication Date: 2011-08-11
    Description: SST air traffic control and arrival and departure simulation
    Keywords: AIRCRAFT
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 10
    facet.materialart.
    Unknown
    Experimental verification of turbulent skin friction reduction with compliant walls (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Preliminary compliant wall skin friction test results obtained in a low-turbulence pressure tunnel are reported. Compliant surface skins consisted of 0.0025 cm thick mylar, stretched under tension and area-bonded or longitudinally strip-bonded with silicone rubber adhesive to polyurethane foam. Mean velocity and fluctuating survey data were obtained with a single slanted hot wire. Mean velocity profiles for the area-bonded mylar surface skins indicated up to a 20% reduction in boundary-layer thickness (and lower momentum thickness) over rigid surfaces. This reduction in boundary-layer thickness indicates that a drag reduction occurred. In addition, a 16% reduction in wall shear was evident for the mylar/compressor foam compliant surface.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal; 13; July 197
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
Close ⊗
This website uses cookies and the analysis tool Matomo. More information can be found here...