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  • AERODYNAMICS  (2,091)
  • Fisheries
  • SPACE SCIENCES
  • 1980-1984  (2,093)
  • 11
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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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  • 12
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    Separation behavior of boundary layers on three-dimensional wings (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An inverse boundary layer procedure for calculating separated, turbulent boundary layers at infinitely long, crabbing wing was developed. The procedure was developed for calculating three dimensional, incompressible turbulent boundary layers was expanded to adiabatic, compressible flows. Example calculations with transsonic wings were made including viscose effects. In this case an approximated calculation method described for areas of separated, turbulent boundary layers, permitting calculation of this displacement thickness. The laminar boundary layer development was calculated with inclined ellipsoids.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75877
    Format: application/pdf
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  • 13
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    Study of the vortex conditions of wings with large sweepback by extrapolation of the Jones method (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The pockets of separation originating on the leading edges are surrounded by vortex sheets. Their configuration and intensity were determined by four conditions with the JONES approximation, which is itself corrected by a simple logic. Field pressures and stresses were computed for different cases and are compared with test results (pure deltas, swallow tails, truncations, strakes, ducks, fuselage).
    Keywords: AERODYNAMICS
    Type: NASA-TM-75863 , Symp. of Appl. Aerodynamics; Nov 13, 1979 - Nov 15, 1979; Lille; France
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  • 14
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    A study of dirigibles for use in the Peruvian Selva Central region (1982)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The potential for dirigibles as transports in the Selva Central region of Peru was evaluated by means of a mission and economic analysis. A total requirement to transport over 19 million tons (t) of agricultural produce, lumber and meat was projected by the year 2004. A primary route involving zones for loading and delivering this carbo was identified. Although dirigibles are capable of short field operation, all existing airfields must be enlarged in width to allow for all conditions of wind and weather and to provide space for overnight mooring. A maintenance base and operations headquarters, complete with hangar and other service facilities would be required. The quantities of cargo capacities of 5 to 100 tons were identified. Fleet sizes up to 106 dirigibles (in 20 t capacities) would be required. Dirigibles were assumed to be of the nonrigid type except in the 100 t category for which rigid characteristics were assumed. A method of determining dirigible costs was developed. The values derived were then applied to an economic analysis to determine initial investment and operating costs. It was found that larger dirigibles of approximately 20 t capacities or higher could offer significant cost benefits over airplanes, provided cruise speeds were higher than 100km/hr.
    Keywords: AERODYNAMICS
    Type: NASA-TM-85634 , NAS 1.15:85634
    Format: application/pdf
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  • 15
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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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  • 16
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    The calculation of separated flow at helicopter bodies (1982)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: For abstract see A81-47555.
    Keywords: AERODYNAMICS
    Type: NASA-TM-76715 , NAS 1.15:76715
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  • 17
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    Lee side flow for slender delta wings of finite thickness (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An experimental and theoretical investigation carried out to determine the lee side flow field over delta wings at supersonic speeds is presented. A theoretical method to described the flow field is described, where boundary conditions as a result of the experimental study are needed. The computed flow field with shock induced separation is satisfactory.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75753 , ILR-23
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  • 18
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    A finite element method for the computation of transonic flow past airfoils (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A finite element method for the computation of the transonic flow with shocks past airfoils is presented using the artificial viscosity concept for the local supersonic regime. Generally, the classic element types do not meet the accuracy requirements of advanced numerical aerodynamics requiring special attention to the choice of an appropriate element. A series of computed pressure distributions exhibits the usefulness of the method.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75749 , MBB-UFE-1352-0
    Format: application/pdf
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  • 19
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    Application of a numerically generated orthogonal coordinate system to the solution of inviscid axisymmetric supersonic flow over blunt bodies (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A numerically generated orthogonal coordinate system (with the body surface and shock wave as opposite boundaries) was applied with a time asymptotic method to obtain steady flow solutions for axisymmetric inviscid flow over several blunt bodies including spheres, paraboloids, ellipsoids, hyperboloids, hemisphere cylinders, spherically blunted cones, and a body with a concavity in the stagnation region. Comparisons with experimental data and with the results of other computational methods are discussed. The numerically generated orthogonal coordinate system is described and applications of the method to complex body shapes, particularly those with concave regions, are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1619 , L-13353
    Format: application/pdf
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  • 20
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    On the flow processes in sharply inclined and stalled airfoils in parallel movement and rotation (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The purpose of this study is to obtain a deeper insight into the complicated flow processes on airfoils in the region of the buoyancy maxima. To this end calculated and experimental investigations are carried out on a straight stationary, a twisted stationary and a straight rotating rectangular wing. According to the available results the method gives results which can be applied sufficiently for flow applied firmly on all sides for all rotation values. The reliability of the method may be questioned for a flow undergoing transition from the attached to the separated state or for totally separated flow and higher rotation values.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77509 , NAS 1.15:77509
    Format: application/pdf
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