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
    Study of multibody aerodynamic interference at transonic Mach numbers (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 26; 553-560
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 2
    facet.materialart.
    Unknown
    An overview of hypersonic aerothermodynamics (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: This paper briefly reviews some national studies and new programs concerning hypersonic flight. The flight environment that will be encountered by this new class of hypersonic vehicles is described, and the fluid-dynamic and chemical phenomena that occur in hypersonic flight are examined. Ground-based facilities are briefly described, and their use in helping to validate the codes is examined.
    Keywords: AERODYNAMICS
    Type: Communications in Applied Numerical Methods (ISSN 0748-8025); 4; 319-325
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 3
    facet.materialart.
    Unknown
    A study of flow separation on an aspect ratio three flap at Mach number 2.4 (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Static pressure distributions and dark central ground interferometry are used to document the flow on a flap over a range of Reynolds numbers and deflection angles. The pressure profiles and interferograms are analyzed to distinguish laminar, transitional and turbulent flows in attached, incipient and separated cases. Sideplates are used to compare two and three dimensional effects. Data is also presented for extended flaps used to isolate the effect of the trailing edge expansion. The issues of unsteadiness and hysteresis are also addressed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-1620
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 4
    facet.materialart.
    Unknown
    Multibody interference at transonic Mach numbers (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An experimental and computational study has been made of the forces and moments on multibody configurations at Mach numbers from 0.6 to 1.2. The interference forces and moments that occur on symmetric double and triple body configurations at zero angle of attack are examined in detail. In all cases, the normal interference force is always in a direction to pull the bodies together and the moment about the 0.5L point is always to rotate the tips of the bodies away from the center of the configuration. The axial interference force (pressure drag at zero angle of attack) increases the drag per store as additional stores are added to the configuration. The effect of angle of attack on the interference is relatively small.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-0651
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 5
    facet.materialart.
    Unknown
    Transonic flow modes of an axisymmetric blunt body (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation of transonic flow past a plane-nosed circular cylinder with a plane-nosed circular probe extended coaxially ahead is reported. The possibilities of significant transonic drag reduction and the fluid mechanic phenomena which occur are examined. The probe length and diameter and the approaching flow Mach number are the independent variables. The relations which exist among the probe/cylinder geometry, Mach number, and flow field as revealed by measurements of the drag forces acting on the body are explored.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-3536
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 6
    facet.materialart.
    Unknown
    Streamlines, vorticity lines, and vortices (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The properties of vortical flows are studied using both theoretical analysis and computational flow fields. The consequences of two definitions of the vortex core, a minimum in the streamline curvature and a maximum in the normalized helicity, are examined. Analysis indicates that several criteria must be met if the cores defined by these two methods are to coincide. In certain regions of the flow, computational flow fields indicate that these two definitions are coincident, that the velocity and vorticity fields are aligned at the core, and that extrema in the velocity magnitude, vorticity magnitude, pressure, and density occur at the core.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-0731
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 7
    facet.materialart.
    Unknown
    A numerical study of flare stabilized projectiles at Mach 7.0 (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The effect of nose shape on two flare stabilized projectiles was studied using a Parabolized Navier-Stokes code. Pressure coefficients, forces and moments, skin friction coefficients, and Stanton number calculations are presented for the hemisphere-cylinder-flare and the cone-cylinder-flare configurations. Pitching moment and static margin plots versus flare angles and flare lengths are presented in a parametric study to show aerodynamic stability effects. Distinctly different flow field values of pressure, local Mach number, and dynamic pressure were generated by the two different nose configurations. These flow field values just upstream of the flare will be examined. The code demonstrated its value as a design tool by making a clear distinction between aerodynamically stable characteristics for this variety of nose shapes, flare angles, and flare lengths.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-0446 , AD-A189212
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 8
    facet.materialart.
    Unknown
    Bifurcations in unsteady aerodynamics-implications for testing (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The various forms of bifurcations that can occur between steady and unsteady aerodynamic flows are reviewed. Examples are provided to illustrate the various ways in which bifurcations may intervene to influence the outcome of dynamics tests involving unsteady aerodynamics. The presence of bifurcation phenomena in such tests must be taken into consideration to ensure the proper interpretation of results, and some recommendations are made to that end.
    Keywords: AERODYNAMICS
    Type: NASA-TM-100083 , A-88076 , NAS 1.15:100083
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 9
    facet.materialart.
    Unknown
    A study of multi-body aerodynamic interference at transonic Mach numbers (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A wind tunnel experiment involving single, double, and triple combinations of mutually interfering generic, unfinned aircraft stores has been conducted. Each combination of stores was tested at Mach numbers from 0.60 to 1.20 and at angles of attack from 0 to 25 deg for the single store and from 0 to 6 deg for the double and triple store configurations. Extensive axial and circumferential pressure and flow visualization data at each store location were obtained. Euler solutions for each configuration at 0 deg incidence have been generated and compared with experimental data. This comparison indicates an Euler flow solver can yield accurate predictions of the location and magnitude of multibody interference provided an appropriate grid is used and the viscous effects associated with these configurations remain small. The data indicate multibody interference in the transonic region increases as the freestream Mach number approaches 1 from either direction, and subsides as the Mach number moves away from sonic conditions. This interference is characterized by a large, localized reduction in pressure on the inboard surfaces of the bodies which results in forces that draw the configuration closer together.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-0519
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 10
    facet.materialart.
    Unknown
    Streamlines, vorticity lines, and vortices around three-dimensional bodies (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 7 Ju; 1819-182
    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...