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  • STRUCTURAL MECHANICS  (79)
  • AERODYNAMICS  (67)
  • ASTROPHYSICS
  • 1970-1974  (117)
  • 1960-1964  (29)
  • 1972  (117)
  • 1964  (29)
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  • 1970-1974  (117)
  • 1960-1964  (29)
Year
  • 1
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    Influence of damping and mass-stiffness discontinuities upon the dynamic stability of a free-free beam under a gimballed thrust of periodically-varying magnitude Technical memorandum no. 103 (1964)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Damping and mass stiffness discontinuity effects on dynamic stability of free-free beam under gimballed pulsating end thrust
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-70054 , E20-117
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    On the starting characteristics of supersonic ejector systems. (1964)
    In:  Other Sources
    Details
    Publication Date: 2019-05-24
    Description: Quasi-steady flow analysis of transient pumping characteristics of supersonic ejector systems
    Keywords: AERODYNAMICS
    Type: ASME PAPER 64-FE-9
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Residual strength and crack propagation tests on C-130 airplane center wings with service-imposed fatigue damage (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Fourteen C-130 airplane center wings, each containing service-imposed fatigue damage resulting from 4000 to 13,000 accumulated flight hours, were tested to determine their fatigue crack propagation and static residual strength characteristics. Eight wings were subjected to a two-step constant amplitude fatigue test prior to static testing. Cracks up to 30 inches long were generated in these tests. Residual static strengths of these wings ranged from 56 to 87 percent of limit load. The remaining six wings containing cracks up to 4 inches long were statically tested as received from field service. Residual static strengths of these wings ranged from 98 to 117 percent of limit load. Damage-tolerant structural design features such as fastener holes, stringers, doublers around door cutouts, and spanwise panel splices proved to be effective in retarding crack propagation.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-2075 , ER-11178
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Safe atmosphere entry of an isotope heat source with a single stable trim attitude at hypersonic speeds (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A theoretical investigation has been made to design an isotope heat source capable of satisfying the conflicting thermal requirements of steady-state operation and atmosphere entry. The isotope heat source must transfer heat efficiently to a heat exchange during normal operation with a power system in space, and in the event of a mission abort, it must survive the thermal environment of atmosphere entry and ground impact without releasing radioactive material. A successful design requires a compatible integration of the internal components of the heat source with the external aerodynamic shape. To this end, configurational, aerodynamic, motion, and thermal analyses were coupled and iterated during atmosphere entries at suborbital through superorbital velocities at very shallow and very steep entry angles. Results indicate that both thermal requirements can be satisfied by a heat source which has a single stable aerodynamic orientation at hypersonic speeds. For such a design, the insulation material required to adequately protect the isotope fuel from entry heating need extend only half way around the fuel capsule on the aerodynamically stable (wind-ward) side of the heat source. Thus, a low-thermal-resistance, conducting heat path is provided on the opposite side of the heat source through which heat can be transferred to an adjacent heat exchanger during normal operation without exceeding specified temperature limits.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6833 , A-4342
    Format: application/pdf
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  • 5
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    Effect of Reynolds number on overall performance of a 3.7-inch-diameter six-stage axial-flow compressor (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A 9.4-centimeter (3.7-in.) diameter six-stage axial-flow compressor was tested in argon over a range of inlet pressures corresponding to a Reynolds number range of 30,600 to 160,000. The effect of Reynolds number on efficiency, pressure ratio, work input, maximum flow, and surge is shown. The Reynolds number effects are discussed in terms of changes in boundary-layer thickness, losses, and the resulting changes in throughflow velocity. Significant deviation was noted from the 0.2 power relation often used to express the variation of loss with Reynolds number.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6628 , E-6522
    Format: application/pdf
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  • 6
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    Optimum mass-strength analysis for orthotropic ring-stiffened cylinders under axial compression (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analysis was developed to calculate the minimum mass-strength curve for an orthotropic cylinder subjected to axial compressive loading. The analysis, which includes the effects of ring and stringer eccentricities, is in a general form so that various cylinder wall and stiffener geometries can be considered. Several different ring-stiffened orthotropic configurations were studied. The minimum mass-strength curves and the dimensions associated with these curves are presented for (in order of decreasing efficiency) a tubular double bead, a nonsymmetric double bead, a Z-stiffened skin, and a trapezoidal corrugation. A comparison of efficiencies of the configurations shows a tubular element cylinder to be more efficient than a 3-percent core-density honeycomb-sandwich cylinder. It was found that for an optimized Z-stiffened skin, the location of the Z-stiffeners (internal or external) made a negligible difference in efficiency.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-6772 , L-7060
    Format: application/pdf
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  • 7
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    Performance of 1380 foot per second tip-speed axial-flow compressor rotor blade tip solidity of 1.5 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This presents the aerodynamic design parameters along with the overall and blade element performance of an axial-flow compressor rotor designed to study the effects of blade solidity on efficiency and stall margin. At design speed the peak efficiency was 0.892 and occurred at an equivalent weight flow of 65.0 lb/sec. The total pressure ratio was 1.83 and the total temperature ratio was 1.215. Design efficiency, weight flow, pressure ratio, and temperature ratio were 0.824, 65.3, 1.65, and 1.187, respectively. Stall margin for design speed was 10 percent based on the weight flow and pressure ratio values at peak efficiency and just prior to stall.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2379 , E-5723
    Format: application/pdf
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  • 8
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    Analysis of the transient response of shell structures by numerical methods. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper examines some basic considerations underlying dynamic shell response analysis and the impact of these considerations upon the practical aspects of solution by numerical methods. Emphasis is placed on the solution of linear problems. The present states of development of the finite difference and finite element methods are reviewed, and techniques for the treatment of temporal variation are discussed. An examination is made of the frequency parameters characteristic of thin shell theory, applied excitations, and spatial mesh geometries, and the significance of these parameters with respect to computational convergence is illustrated.
    Keywords: STRUCTURAL MECHANICS
    Type: Dynamic response of structures; Symposium; Jun 28, 1971 - Jun 29, 1971; Stanford, CA
    Format: text
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  • 9
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    Automated procedures for sizing aerospace vehicle structures /SAVES/ (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Results from a continuing effort to develop automated methods for structural design are described. A system of computer programs presently under development called SAVES is intended to automate the preliminary structural design of a complete aerospace vehicle. Each step in the automated design process of the SAVES system of programs is discussed, with emphasis placed on use of automated routines for generation of finite-element models. The versatility of these routines is demonstrated by structural models generated for a space shuttle orbiter, an advanced technology transport,n hydrogen fueled Mach 3 transport. Illustrative numerical results are presented for the Mach 3 transport wing.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 72-332 , Structures, Structural Dynamics, and Materials Conference; Apr 10, 1972 - Apr 12, 1972; San Antonio, TX
    Format: text
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  • 10
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    Study of induced load and stress, volume 3 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analytical and experimental investigation into the effects of blade tip clearance on inducer performance and of leading edge sweepback on both blade pressure loading and performance was performed. Tip clearance flow was represented with a vortex flow model and measured data from previous inducer tests at three clearances were correlated with model predictions. A leading edge model was added to an existing inducer internal flow analysis, tests with two sweepbacks were conducted, and blade pressure and performance predictions were correlated with measured data.
    Keywords: AERODYNAMICS
    Type: NASA-CR-72712 , PWA-FR-3704-VOL-3
    Format: application/pdf
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