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  • Other Sources  (442)
  • AIRCRAFT PROPULSION AND POWER  (223)
  • STRUCTURAL MECHANICS  (182)
  • Aircraft Stability and Control
  • Cell & Developmental Biology
  • GENERAL
  • General Chemistry
  • Industrial Chemistry
  • 1975-1979  (419)
  • 1955-1959  (23)
  • 1910-1914
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  • 1
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    Full scale upper surface blown flap noise (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A highly noise suppressed TF 34 engine was used to investigate the noise of several powered lift configurations involving upper surface blown (USB) flaps. The configuration variables were nozzle type (i.e. slot and circular with deflector), flap chord length, and flap angle. The results of velocity surveys at both the nozzle exit and the flap trailing edge are also presented and used for correlation of the noise data. Configurations using a long flap design were 4 db quieter than a short flap typical of current trends in USB flap design. The lower noise for the long flap is attributed primarily to the greater velocity decay of the jet at the flap trailing edge. The full-scale data revealed substantially more quadrupole noise in the region near the deflected jet than observed in previous sub-scale tests.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71708 , E-8322 , Natl. Air Transportation Meeting; May 06, 1975 - May 08, 1975; Hartford, CT; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Stability analysis of nonlinear autonomous systems - General theory and application to flutter (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The analysis makes use of a singular perturbation method, the multiple time scaling. Concepts of stable and unstable limit cycles are introduced. The solution is obtained in the form of an asymptotic expansion. Numerical results are presented for the nonlinear flutter of panels and airfoils in supersonic flow. The approach used is an extension of a method for analyzing nonlinear panel flutter reported by Morino (1969).
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 75-102 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    High heat flux actively cooled honeycomb sandwich structural panel for a hypersonic aircraft (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a program to design and fabricate an unshielded actively cooled structural panel for a hypersonic aircraft are presented. The design is an all-aluminum honeycomb sandwich with embedded cooling passages soldered to the inside of the outer moldline skin. The overall finding is that an actively cooled structure appears feasible for application on a hypersonic aircraft, but the fabrication process is complex and some material and manufacturing technology developments are required. Results from the program are summarized and supporting details are presented.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-2959
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Tests of beaded and tubular structural panels (1978)
    In:  CASI
    Details
    Publication Date: 2006-06-12
    Description: Two efficient concepts built from curved elements were identified, and a data base for tubular panels was developed. The tubular panel failure modes were understood, and the data base for these panels indicated that their performance can be predicted. The concepts are currently being tested in a realistic builtup structure; 157 room temperature tests and 67 hot tests were made with no structural failures, although all of these tests were not at the design load of the structure.
    Keywords: STRUCTURAL MECHANICS
    Type: Recent Advan. in Structures for Hypersonic Flight, Pt. 2; p 538-576
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    External-store drag reduction at transonic and low supersonic Mach numbers by application of Baldwin's moment-of-area rule (1955)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: GENERAL
    Type: NACA Conf. on Aerodyn. of High Speed Aircraft; p 93-103
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Effect of endwall cooling on secondary flows in turbine stator vanes (1977)
    In:  CASI
    Details
    Publication Date: 2012-05-19
    Description: An experimental investigation was performed to determine the effect of endwall cooling on the secondary flow behavior and the aerodynamic performance of a coreturbine stator vane. The investigation was conducted in a cold-air, full-annular cascade, where three-dimensional effects could be obtained. Two endwall cooling configurations were tested. In the first configuration, the cooling holes were oriented so that the coolant was injected in line with the inviscid streamline direction. In the second configuration, the coolant was injected at an angle of 15 deg to the inviscid streamline direction and oriented toward the vane pressure surface. In both cases the stator vanes were solid and uncooled so that the effect of endwall cooling could be obtained directly. Total-pressure surveys were taken downstream of the stator vanes over a range of cooling flows at the design, mean-radius, critical velocity ratio of 0.778. Changes in the total-pressure contours downstream of the vanes were used to obtain the effect of endwall cooling on the secondary flows in the stator. Comparisons were made between the two cooled-endwall configurations and with the results obtained previously for solid endwalls.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Secondary Flows in Turbomachines; 29 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    The automated multi-stage substructuring system for NASTRAN (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The substructuring capability developed for eventual installation in Level 16 is now operational in a test version of NASTRAN. Its features are summarized. These include the user-oriented, Case Control type control language, the automated multi-stage matrix processing, the independent direct access data storage facilities, and the static and normal modes solution capabilities. A complete problem analysis sequence is presented with card-by-card description of the user input.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 571-591
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Propulsion system noise reduction (1975)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The progress in propulsion system noise reduction is reviewed. The noise technology areas discussed include: fan noise; advances in suppression including conventional acoustic treatment, high Mach number inlets, and wing shielding; engine core noise; flap noise from both under-the-wing and over-the-wing powered-lift systems; supersonic jet noise suppression; and the NASA program in noise prediction.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 1-63
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    NASTRAN applications to aircraft propulsion systems (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The use of NASTRAN in propulsion system structural integration analysis is described. Computer support programs for modeling, substructuring, and plotting analysis results are discussed. Requirements on interface information and data exchange by participants in a NASTRAN substructure analysis are given. Static and normal modes vibration analysis results are given with comparison to test and other analytical results.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 91-104
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Implementation on a nonlinear concrete cracking algorithm in NASTRAN (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A computer code for the analysis of reinforced concrete structures was developed using NASTRAN as a basis. Nonlinear iteration procedures were developed for obtaining solutions with a wide variety of loading sequences. A direct access file system was used to save results at each load step to restart within the solution module for further analysis. A multi-nested looping capability was implemented to control the iterations and change the loads. The basis for the analysis is a set of mutli-layer plate elements which allow local definition of materials and cracking properties.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Ames Res. Center NASTRAN: User's Experiences; p 479-494
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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