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  • LUNAR AND PLANETARY EXPLORATION  (552)
  • AERODYNAMICS  (479)
  • Animals  (441)
  • Fisheries
  • 1980-1984  (1,473)
  • 1983  (1,473)
  • 1
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    Crater numbers and geological histories of Iapetus, Enceladus, Tethys and Hyperion (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: The surfaces of the Saturn satellites Tethys, Iapetus and Encedalus display surfaces which indicate active geological processes and therefore suggest a degree of internal evolution. By contrast, the Saturn satellite Hyperion and the coorbitals 1980S1 and 1980S3 show no trace of geological activity and may be fragments of once-larger bodies. Activity on Iapetus appears to have been confined to the dark terrain, and offers no clue as to its timing and extent. The widest terrain type and crater number variations are those of Encedalus, which indicate the most prolonged period of geological activity of any of the satellites studied.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Nature; 301; Feb. 24
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Rain and deicing experiments in a wind tunnel (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Comments on films of tests simulating rain and ice conditions in a wind tunnel are presented, with the aim of studying efficient methods of overcoming the adverse effects of rain and ice on aircraft. In the experiments, lifesize models and models of the Mirave 4 aircraft were used. The equipment used to simulate rain and ice is described. Different configurations of landing and takeoff under conditions of moderate or heavy rain at variable angles of incidence and of skipping and at velocities varying from 30 to 130 m/sec are reproduced in the wind tunnel. The risks of erosion of supersonic aircraft by the rain during the loitering and approach phases are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77077 , NAS 1.15:77077 , May 29, 1967 - May 31, 1967; Paris
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Some characteristic quantities of Karman-Trefftz profiles (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: For von Karman-Trefftz profiles, the characteristics which determine profile shape (profile nose dimensions, maximum thickness and position: tail slope and curvature) are stated as a function of transformation variables using the Timman method. The profile is obtained by iterative deformation of a von Karman profile with known transformation, corresponding as well as possible to the desired profile. The figures and relations which enable a good choice of the required profile are given.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77013 , NAS 1.15:77013
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Experimental determination of the inertia constants of an airplane or of a missile (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The possibility to measure the inertia constants of an airplane or of a missile by a unique experimental set up without having to materialize axes of rotation was investigated. It is sufficient to suspend the structure appropriately, to obtain the six natural modes determined by the suspension and to introduce these results as data into a computer. If the structure is very flexible it is necessary to take into account the first natural modes of deformation. Experiments on rigid and flexible models led to precise results and allow consideration of full scale measurements. The final goal is to provide, by a standard ground vibration test completed by the measured characteristics of the suspension modes, the set of data necessary for flutter calculations and for the determination of all the inertia constants.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77767 , NAS 1.15:77767
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Construction of a model of the Venus surface and its use in processing radar observations (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An algorithm is described for constructing the model of the Venus surface as an expansion in spherical functions. The relief expansion coefficients were obtained up to the coefficient S sub 99. The surface picture representation is given according to this expansion. The surface model constructed was used for processing radar observations. The use of the surface model allows improved agreement between the design and measured values of radar ranges.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: NASA-TM-77298 , NAS 1.15:77298
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Reduction of the shock wave intensity by modifying the transonic blade trailing edge (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: It is shown that the shock wave intensity can be decreased by using modified trailing edge configurations to reduce or even completely compensate for the effect of the finite thickness of the trailing edge. A theoretical analysis is presented together with numerical results for two supersonic streams flowing off the trailing edge at different velocities. The analysis is based on an ideal gas model.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77029 , NAS 1.15:77029
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Flow mechanism and experimental investigation of a rotating stall in transonic compressors (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The flow characteristics of the rotating stall in compressors is studied, and a flow model is developed along with a theoretical calculation method based on vortex theory. A detailed theoretical calculation is completed for a two dimensional flow field in a transonic rotor in a rotating stall, and the result is in good agreement with experimental findings. The oscillograms of time-varying stall characteristic parameters recorded for the onset, growth, and cessation processes of rotating stall are analyzed, and some new flow phenomena deserving of further investigation are discovered. These include serious separation of individual blades, often preceding the onset of rotating stall in compressors with very small blade-camber angles, and periodical variation of the circumferential width of the stall cell with time, accompanied by periodical oscillation of the width of the stall cell in the radial direction of the blade. The circumferential and radial oscillation frequencies are the same.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77373 , NAS 1.15:77373
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Wind tunnel investigations of glider fuselages with different waistings and wing arrangements (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The parameters fuselage pinch glider wing arrangement and fuselage leading edge radius of nine glider configurations were investigated in wind tunnel tests. Laminar separation bubbles were found on strongly recessed fuselages. These separations in the juncture between fuselage and wing are essential in the prevention of harmful aerodynamic drag. Drag reduction was measured with increasing pinch and the wing arrangement in the rear. These results are only valid for laminar flow on the fuselage leading edge.
    Keywords: AERODYNAMICS
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Etching of moldavities under natural conditions (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The hypothesis that a part of the lechatellierites which originated by etching from a basic moldavite mass became broken off after deposition of moldavite in the sedimentation layer is advanced. Those found close to the original moldavite were measured for statistical averaging of length. The average length of lechatelierite fibers per cubic mm of moldavite mass volume was determined by measurement under a microscope in toluene. The data were used to calculate the depth of the moldavite layer that had to be etched to produce the corresponding amount of lechatelierite fragments. The calculations from five "fields" of moldavite surface, where layers of fixed lechatelierite fragments were preserved, produced values of 2.0, 3.1, 3.5, 3.9 and 4.5. Due to inadvertent loss of some fragments the determined values are somewhat lower than those found in references. The difference may be explained by the fact that the depth of the layer is only that caused by etching after moldavite deposition.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: NASA-TM-77334 , NAS 1.15:77334
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Laminarization of a boundary layer in a supersonic nozzle by cooling of the surface (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The concept of cooling of the surface of wind tunnel walls in order to laminarize the boundary layer, and thereby eliminate perturbations in the working area, is discussed. Equations are given, which are used to calculate the temperature conditions under which the flow in the boundary layer will be stably laminar.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77341 , NAS 1.15:77341
    Format: application/pdf
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