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
Filter
  • AERODYNAMICS  (58)
  • 2020-2024
  • 1975-1979  (58)
  • 1955-1959
  • 1978  (58)
  • 1
    facet.materialart.
    Unknown
    Effects of wing leading-edge deflection on the low-speed aerodynamic characteristics of a low-aspect-ratio highly swept arrow-wing configuration (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wing leading-edge deflection effects on the low-speed aerodynamic characteristics of a low-aspect-ratio highly swept arrow-wing configuration were determined. Static force tests were conducted in a V/STOL tunnel at a Reynolds number of about 2.5 x 1 million for an angle-of-attack range from -10 deg to 17 deg and an angle-of-sideslip range from -5 deg to 5 deg. Limited flow visualization studies were also conducted in order to provide a qualitative assessment of leading-edge upwash characteristics.
    Keywords: AERODYNAMICS
    Type: NASA-TM-78787
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 2
    facet.materialart.
    Unknown
    Injection slot location for boundary-layer control in shock-induced separation (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An experimental investigation of the effect of tangential air injection, when the injection slot is located inside of what would otherwise have been the dead air zone in a separated flow, in controlling shock-induced turbulent boundary layer separation is presented. The experiments were carried out at a free-stream Mach number of 2.5 in the separated flow induced by a compression corner with a 20 deg angle. The observations made were wall static pressures, pitot profiles, and schlieren visualizations of the flow. The results show that the present location for injection is more effective in suppressing boundary-layer separation than the more conventional one, where the slot is located upstream of where separation would occur in the absence of injection.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-1168 , Fluid and Plasma Dynamics Conference; Jul 10, 1978 - Jul 12, 1978; Seattle, WA
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 3
    facet.materialart.
    Unknown
    Propeller slipstream wing interactions at Mach no. 0.8 (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Configuration and results of a wind tunnel test of the aerodynamic interactions between propeller slipstream and a supercritical wing at transonic Mach numbers are discussed. The test was conducted over a free-stream Mach number range from 0.7 to 0.84, with the slipstream simulator and the wing-body model installed in the tunnel. The angle of attack and the spanning lift coefficients were varied from 1 to 3 deg and from 0.4 to 0.7 deg respectively, while the slipstream swirl angle was varied from 0 to 11 deg with an upwash on the inboard side of the wing. It was found that at a free-stream Mach number of 0.8 and a lift coefficient of 0.5, incremental drag results for 7 deg of swirl and a slipstream Mach number of 0.87 indicated a penalty equivalent to a 0.024 loss in propeller efficiency, whereas at 11 deg the drag increment was favorable. Swirl had significant effects on the chordwise pressure distributions of the inboard section of the wing within the slipstream. Neither surface nor wake pressures showed signs of significant flow separation induced by the slipstream.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 780997 , Society of Automotive Engineers, Aerospace Meeting; Nov 27, 1978 - Nov 30, 1978; San Diego, CA
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 4
    facet.materialart.
    Unknown
    Section drag coefficients from pressure probe transverses of a wing wake at low speeds (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: An in-flight wing wake section drag investigation was conducted using traversing pitot and static probes. The primary objective was to develop measurement techniques and improve the accuracy of in-flight wing profile drag measurements for low values of dynamic pressure and Reynolds number. Data were obtained on a sailplane for speeds from about 40 knots to 125 knots at chord Reynolds numbers between 1,000,000 and 3,000,000. Tests were conducted with zero flap deflection, deflected flaps, and various degrees of surface roughness, and for smooth and rough atmospheric conditions. Several techniques were used to increase data reliability and to minimize certain bias errors. A discussion of the effects of a total pressure probe in a pressure gradient, and the effects of discrete turbulence levels, on the data presented and other experimental results is also included.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 601-621
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 5
    facet.materialart.
    Unknown
    Inlet boundary-layer shapes on four aircraft forebodies at Mach 6 (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Boundary-layer shape measurements at the engine inlet on four different hypersonic aircraft forebody designs (with no engine on the forebody) are reported. The measurements provide a qualitative assessment of the effectiveness of various forebody geometries as engine inlet precompression surfaces. The designs, tested in a hypersonic tunnel at Mach 6 and a nominal freestream Reynolds number of 30,500,000, included a semiconical forebody, a configuration similar to a slab delta wing, a conical nose blended into a flat surface, and a conical, complex forebody shape. Boundary layer height as a function of forebody compression is shown for each design.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 15; Jan. 197
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 6
    facet.materialart.
    Unknown
    Summary of system state-of-health measurements STRATCOM 8: A balloon experiment (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Various measurements were made to determine the temperature and attitude of the gondola and the status of primary power and control equipment. Bead thermistors were used to measure temperatures at selected points throughout the gondola. A two-axis magnetometer and a two-axis pendulum were used to measure gondola attitude. Voltage and current measurements indicated the status of the primary power sources and associated power converters.
    Keywords: AERODYNAMICS
    Type: NASA. Goddard Space Flight Center STRATCOM 8 Data Workshop and Suppl.; p 24-31
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 7
    facet.materialart.
    Unknown
    Interaction of a two-dimensional strip boundary layer with a three-dimensional transonic swept-wing code (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A 3D inviscid transonic analysis code was combined with a 2D strip integral boundary layer technique to form an approximate interaction procedure for analyzing the flow over a high aspect ratio wing near cruise conditions. Converged results obtained using the procedure for an aspect ratio 10.3 supercritical wing are discussed. Angle of attack adjustments were made during the iterative procedure in order to compensate for the viscous lift loss. A comparison of the calculations with experimental data is presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-78640
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 8
    facet.materialart.
    Unknown
    REXOR 2 rotorcraft simulation model. Volume 3: User's manual (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N78-30042.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145333 , LR-28435-VOL-3
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 9
    facet.materialart.
    Unknown
    REXOR 2 rotorcraft simulation model. Volume 1: Engineering documentation (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A rotorcraft nonlinear simulation called REXOR II, divided into three volumes, is described. The first volume is a development of rotorcraft mechanics and aerodynamics. The second is a development and explanation of the computer code required to implement the equations of motion. The third volume is a user's manual, and contains a description of code input/output as well as operating instructions.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145331 , LR-28435-VOL-1
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 10
    facet.materialart.
    Unknown
    Wing analysis using a transonic potential flow computational method (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The ability of the method to compute wing transonic performance was determined by comparing computed results with both experimental data and results computed by other theoretical procedures. Both pressure distributions and aerodynamic forces were evaluated. Comparisons indicated that the method is a significant improvement in transonic wing analysis capability. In particular, the computational method generally calculated the correct development of three-dimensional pressure distributions from subcritical to transonic conditions. Complicated, multiple shocked flows observed experimentally were reproduced computationally. The ability to identify the effects of design modifications was demonstrated both in terms of pressure distributions and shock drag characteristics.
    Keywords: AERODYNAMICS
    Type: NASA-TM-78464 , A-7308
    Format: application/pdf
    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...