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  • AERODYNAMICS  (851)
  • 1980-1984  (851)
  • 1984  (485)
  • 1981  (366)
  • 1
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    Current developments lighter than air systems (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Lighter than air aircraft (LTA) developments and research in the United States and other countries are reviewed. The emphasis in the U.S. is on VTOL airships capable of heavy lift, and on long endurance types for coastal maritime patrol. Design concepts include hybrids which combine heavier than air and LTA components and characteristics. Research programs are concentrated on aerodynamics, flight dynamics, and control of hybrid types.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84744 , NAS 1.15:84744
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Experimental investigation of the flow on the suction side of a thin Delta wing (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Surface oil flow patterns were photographed and pressure distribution measurements were carried out on a sharp edged delta wing of aspect ratio lambda = 1.0 in order to determine the influence of Reynolds number and of vortex breakdown on the flow on the suction side of the wing. The formation of the secondary vortex occurs due to separation of a laminar boundary layer in the front part of the wing and due to separation of a turbulent boundary layer in the rear part of the wing. In the case of turbulent separation, the secondary separation line is closer to the wing leading edge than in the laminar case. The position of the transition depends on the Reynolds number and on the angle of incidence. The breakdown of a vortex above the wing leads to a kink in the secondary separation line.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75897
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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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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    NASA TECHNICAL REPORTS
  • 4
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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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  • 5
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    A new method of evaluating the side wall interference effect on airfoil angle of attack by suction from the side walls (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A quantitative evaluation method of the suction effect from a suction plate on side walls is explained. It is found from wind tunnel tests that the wall interference is basically described by the summation form of wall interferences in the case of two dimensional flow and the interference of side walls.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77722 , NAS 1.15:77722 , NAL-TR-680
    Format: application/pdf
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  • 6
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    A possibility of avoiding surface roughness due to insects (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Discussion of a method for eliminating turbulence caused by the formation of insect roughness upon the leading edges and fuselage, particularly in aircraft using BLC. The proposed technique foresees the use of elastic surfaces on which insect roughness cannot form. The operational characteristics of highly elastic rubber surface fastened to the wing leading edges and fuselage edges are examined. Some preliminary test results are presented. The technique is seen to be advantageous primarily for short-haul operations.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77419 , NAS 1.15:77419 , Feb 01, 1963 - Feb 28, 1963; Junin; Argentina
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  • 7
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    Kasprzyk airfoil. The first wind-tunnel tests (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The Kasprzyk slotted flap glider airfoil (the Kasper wing) enabling glider flight at 32 km/h and 0.5 m/sec descent speed was wind tunnel tested in the U.S. The test layout is described and reasons offered for discrepancies between wind tunnel results and Polish in flight data: high induced drag caused by relative size of model wing span and tunnel, by vortex attenuators on the model and their proximity to the tunnel wall, nonsimilarity between flow over a smooth wing and flow over the Kasprzyk wing with bound vortices, obstruction of the tunnel test chamber cross section by the model wing, discrepant Reynolds numbers, and model airfoil aspect ratio much smaller than the prototype. The overall results offer partial confirmation of the Kasprzyk theory, but further in tunnel and in flight studies are recommended.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77757 , NAS 1.15:77757
    Format: application/pdf
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  • 8
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    Analysis of airfoil transitional separation bubbles (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A previously developed local inviscid-viscous interaction technique for the analysis of airfoil transitional separation bubbles, ALESEP (Airfoil Leading Edge Separation) has been modified to utilize a more accurate windward finite difference procedure in the reversed flow region, and a natural transition/turbulence model has been incorporated for the prediction of transition within the separation bubble. Numerous calculations and experimental comparisons are presented to demonstrate the effects of the windward differencing scheme and the natural transition/turbulence model. Grid sensitivity and convergence capabilities of this inviscid-viscous interaction technique are briefly addressed. A major contribution of this report is that with the use of windward differencing, a second, counter-rotating eddy has been found to exist in the wall layer of the primary separation bubble.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3791 , NAS 1.26:3791
    Format: application/pdf
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  • 9
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    Cold-air performance of compressor-drive turbine of department of energy upgraded automobile gas turbine engine. 3: Performance of redesigned turbine (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The aerodynamic performance of a redesigned compressor drive turbine of the gas turbine engine is determined in air at nominal inlet conditions of 325 K and 0.8 bar absolute. The turbine is designed with a lower flow factor, higher rotor reaction and a redesigned inlet volute compared to the first turbine. Comparisons between this turbine and the originally designed turbine show about 2.3 percentage points improvement in efficiency at the same rotor tip clearance. Two versions of the same rotor are tested: (1) an as cast rotor, and (2) the same rotor with reduced surface roughness. The effect of reducing surface roughness is about one half percentage point improvement in efficiency. Tests made to determine the effect of Reynolds number on the turbine performance show no effect for the range from 100,000 to 500,000.
    Keywords: AERODYNAMICS
    Type: NASA-TM-83627 , E-2044 , DOE/NASA/50194-39 , NAS 1.15:83627 , USAAVSCOM-TR-84-C-7
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  • 10
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    Kinematics, influence functions and field quantities for disturbance propagation from moving disturbance sources (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A unified method is presented for deriving the influence functions of moving singularities which determine the field quantities in aerodynamics and aeroacoustics. The moving singularities comprise volume and surface distributions having arbitrary orientations in space and to the trajectory. Hence one generally valid formula for the influence functions which reveal some universal relationships and remarkable properties in the disturbance fields. The derivations used are completely consistent with the physical processes in the propagation field, such that treatment renders new descriptions for some standard concepts. The treatment is uniformly valid for subsonic and supersonic Mach numbers.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77410 , NAS 1.15:77410 , DFVLR-FB-83-01
    Format: application/pdf
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