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  • AERODYNAMICS  (366)
  • Biochemistry and Biotechnology
  • 1980-1984  (684)
  • 1981  (684)
  • 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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    Highly separated transonic flows (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Attention is given to the wind tunnel, to photographic visualization of the flow, and to measurements by pressure probes, hot wire anemometry and laser anemometry. The simultaneous use of different means of measurement provided a good description of the phenomenon, and indicated the existence of shocks and their stability, as well as the existence of the bubble, its dimensions, and in particular, the reattachment of its front. The results show that the bursting (or transition) of the bubble front is produced at an unstable position and creates a point of turbulent intensity which diffuses over the entire height of the flow.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75874 , NT80-18 , Colloq. Aerodyn. Appl.; Nov 13, 1979 - Nov 15, 1979; Lille; France
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  • 5
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    Experimental investigation of a transonic potential flow around a symmetric airfoil (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Experimental flow investigations on smooth airfoils were done using numerical solutions for transonic airfoil streaming with shockless supersonic range. The experimental flow reproduced essential sections of the theoretically computed frictionless solution. Agreement is better in the expansion part of the of the flow than in the compression part. The flow was nearly stationary in the entire velocity range investigated.
    Keywords: AERODYNAMICS
    Type: NASA-TM-76676 , REPT-10/1971
    Format: application/pdf
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  • 6
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    Reduction of profile drag by blowing out through peg holes in areas of streamline separation bubbles (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Streamline separation bubbles on aircraft profiles and fuselages were investigated. The additional drag was examined in relation to increased angle of incidence and unusually high wall sheer stress. A reduction of the separation bubble and a decrease in drag is obtained with pneumatic turbulators that blow ram air out of 0.6mm pilot tubes at a distance of 16 mm. The pneumatic models are implemented at various positions and are found to be effective after the position of separation.
    Keywords: AERODYNAMICS
    Type: NASA-TM-76603 , DGLR-80-103 , Symp. on Aerodynamischen Widerstand; Nov 25, 1980 - Nov 26, 1980; Cologne; Germany
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  • 7
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    The elaboration of a new family of helicopter blade profiles (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: An airfoil family of helicopter rotor blades was designed. Three airfoils with thickness to chord ratios of 12, 9, and 7% were designed. Their improved performance in two dimensional rotor mockup wind tunnel tests led to testing of the tapered blades on four bladed rotors in a wind tunnel and flight tests on the Dauphin series of helicopters, confirming the expected gains.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75907
    Format: application/pdf
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  • 8
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    Flow and Acoustic Properties of Low Reynolds Number Underexpanded Supersonic Jets (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Jet noise on underexpanded supersonic jets are studied with emphasis on determining the role played by large scale organized flow fluctuations in the flow and acoustic processes. The experimental conditions of the study were chosen as low Reynolds number (Re=8,000) Mach 1.4 and 2.1, and moderate Reynolds number (Re=68,000) Mach 1.6 underexpanded supersonic jets exhausting from convergent nozzles. At these chosen conditions, detailed experimental measurements were performed to improve the understanding of the flow and acoustic properties of underexpanded supersonic jets.
    Keywords: AERODYNAMICS
    Type: NASA-CR-169257 , NAS 1.26:169257
    Format: application/pdf
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  • 9
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    Three-dimensional separated flows past ground vehicles (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The separated flow past a thick body is calculated using a theoretical model based on a discrete wake-vortex representation. Rehbach's unsteady inviscid scheme (1977) was used in the three-dimensional analysis. The obstacle is represented by singularities, and the wake is modeled by vortex particles emitted at the separation line. Calculated results for an axisymmetric body are compared with flow visualization results.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75899 , Colloq. d''Aerodynamique Appl.; Nov 13, 1979 - Nov 15, 1979; Lille; France
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    NASA TECHNICAL REPORTS
  • 10
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    Experimental study of the interaction between the wing of a subsonic aircraft and a nacelle of a high by-pass ratio engine (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The oncoming of a new generation of subsonic transport aircraft (with supercritical wing and high by-pass ratio turbofans) led to an experimental study of wing nacelle jet pylon interference in transonic flow. To this end, a test set-up was developed at the ONERA S3Ch wind tunnel. The nacelle models represent a turbofan by means of two compressed air jets. The scale is 1/18.5. The nacelles are fixed on a thrust balance measuring afterbody thrust and discharge coefficients. The wing is located between the sidewalls of the test section. Pressures are measured through 456 holes located on 8 airfoils. Drag coefficient of the wing is obtained by wake survey. The following parameters can vary (1) wing/nacelle position; (2) upstream Mach number (from 0.3 to 0.8); (3) jet pressure ratio; (4) with/without pylon and (5) type of nacelle. Wing nacelle interference can be studied by means of total thrust drag analysis as a functon of the various parameters. The test set-up is described and examples of results are presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-76606 , May 05, 1980 - May 07, 1980; Munich; Germany
    Format: application/pdf
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