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  • STRUCTURAL MECHANICS  (70)
  • FLUID MECHANICS  (62)
  • ASTROPHYSICS
  • 1970-1974  (94)
  • 1960-1964  (38)
  • 1972  (94)
  • 1962  (38)
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  • 1970-1974  (94)
  • 1960-1964  (38)
Year
  • 1
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    DISPERSION OF LONG-PERIOD LOVE WAVES IN A SPHERICAL EARTH (1962)
    In:  CASI
    Details
    Publication Date: 2008-08-25
    Description: Dispersion of waves in a spherical earth
    Keywords: FLUID MECHANICS
    Type: JPL-TR-32-330
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    THE UTILITY OF WEATHER FORECASTS TO THE RAISIN INDUSTRY (1962)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Description: Utility of weather forecasts to the raisin industry
    Keywords: FLUID MECHANICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    THE ADIABATIC INTEGRAL INVARIANT IN THE GEOMAGNETIC FIELD (1962)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Adiabatic integral invariant in the geomagnetic field
    Keywords: FLUID MECHANICS
    Type: RM-3347-NASA
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    THE VERTICAL DISTRIBUTION OF E-REGION IRREGULARITIES DEDUCED FROM SCINTILLATIONS OF SATELLITE RADIO SIGNALS (1962)
    In:  Other Sources
    Details
    Publication Date: 2019-05-11
    Description: Scintillation of radio transmissions from discoverer 38 to determine the existance and nature of diffracting e-region irregularities
    Keywords: FLUID MECHANICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    A study of nozzle and ejector flow problems by the method of integral relations (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The application of the method of integral relations to nozzle and ejector flow problems was examined. For nozzle flow problems, the general formulation is that the approaching flow may be rotational. Particular attention was given to the phenomenon of choking under nonuniform flow conditions. Numerical integration of the governing ordinary differential equations was also investigated. This scheme of analysis was also applied to study the interacting flow field within an ejector system.
    Keywords: FLUID MECHANICS
    Type: NASA-CR-128066 , UILU-ENG-72-4002 , ME-TR-395-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Numerical solutions of several reflected shock-wave flow fields with nonequilibrium chemical reactions (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The method of characteristics for a chemically reacting gas is used in the construction of the time-dependent, one-dimensional flow field resulting from the normal reflection of an incident shock wave at the end wall of a shock tube. Nonequilibrium chemical reactions are allowed behind both the incident and reflected shock waves. All the solutions are evaluated for oxygen, but the results are generally representative of any inviscid, nonconducting, and nonradiating diatomic gas. The solutions clearly show that: (1) both the incident- and reflected-shock chemical relaxation times are important in governing the time to attain steady state thermodynamic properties; and (2) adjacent to the end wall, an excess-entropy layer develops wherein the steady state values of all the thermodynamic variables except pressure differ significantly from their corresponding Rankine-Hugoniot equilibrium values.
    Keywords: FLUID MECHANICS
    Type: NASA-TN-D-6885 , A-4226
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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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
  • 8
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    A study of internal drag of small-scale ducts at Mach number 4 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was made to examine the applicability of methods used to determine internal drag of small ducts and to study some of the problems encountered in assessing momentum losses in such ducts. Test Mach numbers ranged from 3.7 to 4.4 at angles of attack of 0 and 5 degrees and at a constant Reynolds number of 4.3 million per foot. The configurations represented small ducts used to simulate external aerodynamics of air breathing propulsion systems and consisted of wing nacelle models of ducts with circular, square, and rectangular inlets and with a two-dimensional inlet.
    Keywords: FLUID MECHANICS
    Type: NASA-TM-X-62143
    Format: application/pdf
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  • 9
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    An implicit finite-difference solution to the viscous shock layer, including the effects of radiation and strong blowing (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An implicit finite-difference scheme is developed for the fully coupled solution of the viscous, radiating stagnation-streamline equations, including strong blowing. Solutions are presented for both air injection and injection of carbon-phenolic ablation products into air at conditions near the peak radiative heating point in an earth entry trajectory from interplanetary return missions. A detailed radiative-transport code that accounts for the important radiative exchange processes for gaseous mixtures in local thermodynamic and chemical equilibrium is utilized in the study. With minimum number of assumptions for the initially unknown parameters and profile distributions, convergent solutions to the full stagnation-line equations are rapidly obtained by a method of successive approximations. Damping of selected profiles is required to aid convergence of the solutions for massive blowing. It is shown that certain finite-difference approximations to the governing differential equations stabilize and improve the solutions. Detailed comparisons are made with the numerical results of previous investigations. Results of the present study indicate lower radiative heat fluxes at the wall for carbonphenolic ablation than previously predicted.
    Keywords: FLUID MECHANICS
    Type: NASA-TR-R-388 , L-8302
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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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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