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  • STRUCTURAL MECHANICS  (121)
  • PROPULSION SYSTEMS  (118)
  • ASTROPHYSICS
  • 1970-1974  (239)
  • 1972  (109)
  • 1971  (130)
Collection
Keywords
Years
  • 1970-1974  (239)
Year
  • 1
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    Thick high aspect ratio wing, part 2 (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Transonic flutter and buffeting for elastic wind tunnel models of straight wing proposed for space shuttles
    Keywords: STRUCTURAL MECHANICS
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 201-229
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    V/STOL propulsion (1971)
    In:  CASI
    Details
    Publication Date: 2006-04-20
    Description: Propulsion technology for STOL and V/STOL commercial aircraft
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 135-168
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Response of an acoustically loaded panel excited by supersonically convected turbulence (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Structural panel under acoustic loading by supersonic convected turbulence, deriving responses with finite Fourier transforms
    Keywords: STRUCTURAL MECHANICS
    Type: ; - DISCRETE CONTROL S
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Measurements of the response of a panel excited by shock boundary-layer interaction (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Plate excitation by supersonic turbulent and shock boundary layers, measuring wall pressure fluctuation and panel displacement
    Keywords: STRUCTURAL MECHANICS
    Type: ; - DISCRETE CONTROL S
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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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
  • 6
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    Upper-stage space shuttle propulsion by means of separate scramjet and rocket engines (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A preliminary mission study of a reusable vehicle from staging to orbit indicates payload advantages for a dual-propulsion system consisting of separate scramjet and rocket engines. In the analysis the scramjet operated continuously and the initiation of rocket operation was varied. For a stage weight of 500,000 lb the payload was 10.4 percent of stage weight or 70 percent greater than that of a comparable all-rocket-powered stage. When compared with a reusable two-state rocket vehicle having 50,000 lb payload, the use of the dual propulsion system for the second stage resulted in significant decreases in lift-off weight and empty weight, indicating possible lower hardware costs.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-6762 , E-6555
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Jet-noise reduction through liquid-base foam injection. (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation has been made of the sound-absorbing properties of liquid-base foams and of their ability to reduce jet noise. Protein, detergent, and polymer foaming agents were used in water solutions. A method of foam generation was developed to permit systematic variation of the foam density. The investigation included measurements of sound-absorption coefficents for both plane normal incidence waves and diffuse sound fields. The intrinsic acoustic properties of foam, e.g., the characteristic impedance and the propagation constant, were also determined. The sound emitted by a 1-in.-diam cold nitrogen jet was measured for subsonic (300 m/sec) and supersonic (422 m/sec) jets, with and without foam injection. Noise reductions up to 10 PNdB were measured.
    Keywords: PROPULSION SYSTEMS
    Type: Acoustical Society of America; vol. 50
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    C-130: Results of center wing residual strength and crack propagation test program (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Fourteen C-130 airplane center wings which had experienced from approximately 4,000 to 13,000 hours of flight service and its associated fatigue damage were tested to destruction, seven in upbending and seven in downbending. Six wings were tested directly for static residual strength in the fatigue-damaged condition as received from field service. The other eight wings were tested in crack propagation cyclic testing at a prescribed stress level for a maximum of 10,000 cycles. Then the stress level was reduced and testing was continued up to a maximum of 20,000 total cycles. Cyclic testing was performed with constant-amplitude stresses at a stress ratio of +0.1. Maximum cyclic skin stresses were approximately 18,000 psi. At the conclusion of cyclic testing, a static test to destruction was conducted to determine the residual strength of each fatigue-damaged specimen.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-112008 , ER-11178 , LSR-7221-70-012A
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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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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    NASA TECHNICAL REPORTS
  • 10
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    Supersonic flutter of sandwich panels - Effects of face sheet bending stiffness, rotary inertia, and orthotropic core shear stiffnesses (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Numerical analysis of supersonic flutter of flat rectangular, biaxilly stressed sandwich panels
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-6427 , A-3868
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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