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  • AERODYNAMICS  (460)
  • Fisheries
  • 2020-2023
  • 1975-1979  (460)
  • 1950-1954
  • 1976  (460)
  • 1
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    The technology assessment of LTA aircraft systems (1976)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The advantages of conventional small and large airships over heavier than air aircraft are reviewed and the need for developing hybrid aircraft for passenger and heavy charge transport is assessed. Performance requirements and estimated operating costs are discussed for rota-ships to be used for short distance transportation near large cities as well as for airlifting civil engineering machinery and supplies for the construction of power stations, dams, tunnels, and roads in remote areas or on isolated islands.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75535
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    The Effects of Blowing Over Various Trailing-edge Flaps on an NACA 0006 Airfoil Section, Comparisons with Various Types of Flaps on other Airfoil Sections, and an Analysis of Flow and Power Relationships for Blowing Systems (1976)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: The results are presented of a two-dimensional investigation conducted to determine the effect of blowing over various types of trailing-edge flaps on a wing having the NACA 0006 airfoil section and a drooped-nose flap. The position and profile of the trailing-edge flap, the nozzle height, and the location of the flap with respect to the nozzle were found to be important variables. Data from many investigations were used to make an evaluation of the effects of blowing on lift. An analysis was made of flow and power relationships for blowing systems.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8293 , A-6423
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Numerical Airfoil Optimization Using a Reduced Number of Design Coordinates (1976)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: A method is presented for numerical airfoil optimization whereby a reduced number of design coordinates are used to define the airfoil shape. The approach is to define the airfoil as a linear combination of shapes. These basic shapes may be analytically or numerically defined, allowing the designer to use his insight to propose candidate designs. The design problem becomes one of determining the participation of each such function in defining the optimum airfoil. Examples are presented for two-dimensional airfoil design and are compared with previous results based on a polynomial representation of the airfoil shape. Four existing NACA airfoils are used as basic shapes. Solutions equivalent to previous results are achieved with a factor of more than 3 improvements in efficiency, while superior designs are demonstrated with an efficiency greater than 2 over previous methods. With this shape definition, the optimization process is shown to exploit the simplifying assumptions in the inviscid aerodynamic analysis used here, thus demonstrating the need to use more advanced aerodynamics for airfoil optimization.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-73151 , A-6671
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Prediction of longitudinal aerodynamic characteristics of STOL configurations with externally blown high lift devices (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: A theoretical method has been developed to predict the longitudinal aerodynamic characteristics of engine-wing-flap combinations with externally blown flaps (EBF) and upper surface blowing (USB) high lift devices. Potential flow models of the lifting surfaces and the jet wake are combined to calculate the induced interference of the engine wakes on the lifting surfaces. The engine wakes may be circular, elliptic, or rectangular cross-sectional jets, and the lifting surfaces are comprised of a wing with multiple-slotted trailing-edge flaps or a deflected trailing-edge Coanda surface. Results are presented showing comparisons of measured and predicted forces, pitching moments, span-load distributions, and flow fields.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 76-934 , Aircraft Systems and Technology Meeting; Sept. 27-29, 1976; Dallas, TX
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Prediction methods for jet V/STOL propulsion aerodynamics (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The current status of prediction methods for propulsive flows and propulsion-induced effects which occur on jet V/STOL aircraft is reviewed. Among the major topics studied are flows in propulsive ducts, propulsion-induced ground and thermal effects, aerodynamic loads induced during V/STOL and transition flight, flow vectoring devices, and thrust augmented ejector and lift-fan studies. The current predictive capability in jet V/STOL propulsion aerodynamics is assessed. Future research needs are identified, with particular reference to activities that can improve the usefulness of prediction methods for jet V/STOL aircraft.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 76-932 , Aircraft Systems and Technology Meeting; Sept. 27-29, 1976; Dallas, TX
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Powered-Lift Aerodynamics and Acoustics (1976)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Powered lift technology is reviewed. Topics covered include: (1) high lift aerodynamics; (2) high speed and cruise aerodynamics; (3) acoustics; (4) propulsion aerodynamics and acoustics; (5) aerodynamic and acoustic loads; and (6) full-scale and flight research.
    Keywords: AERODYNAMICS
    Type: NASA-SP-406 , Powered-Lift Aerodynamics and Acoustics; May 01, 1976; Hampton, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Quasi-three-dimensional laminar boundary-layer separations in supersonic flow (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A numerical algorithm is presented for solving laminar, steady, supersonic interacting boundary-layer flows for quasi-three-dimensional configurations. The interaction problem is treated as a boundary-value problem and a salient feature of the scheme is the direct implementation of the downstream boundary condition. Solutions are presented for axisymmetric and swept (yawed) compression ramps for both adiabatic and heat transfer conditions over a Mach number range of 2-6. The results are in good agreement with experimental data and existing theories for axisymmetric cases. For the swept (yawed) configurations, lack of experimental data makes a direct comparison impossible, but the present solutions are found to be in qualitative agreement with earlier studies. In addition it is shown that the trends obtained here for the sweep effects are well predicted by a simple extension of the two-dimensional asymptotic theory.
    Keywords: AERODYNAMICS
    Type: Winter Annual Meeting on Numerical/laboratory computer methods in fluid mechanics; Dec 05, 1976 - Dec 10, 1976; New York, NY
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    On some structure-turbulence interaction problems (1976)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The interactions between a turbulent flow structure; responding to its excitation were studied. The turbulence was typical of those associated with a boundary layer, having a cross-spectral density indicative of convection and statistical decay. A number of structural models were considered. Among the one-dimensional models were an unsupported infinite beam and a periodically supported infinite beam. The fuselage construction of an aircraft was then considered. For the two-dimensional case a simple membrane was used to illustrate the type of formulation applicable to most two-dimensional structures. Both the one-dimensional and two-dimensional structures studied were backed by a cavity filled with an initially quiescent fluid to simulate the acoustic environment when the structure forms one side of a cabin of a sea vessel or aircraft.
    Keywords: AERODYNAMICS
    Type: NASA-CR-149461
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    New developments in blown flap noise technology (1976)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The noise technology relating to blown-flap systems is reviewed. There are three general sources of noise: turbomachinery, airframe, and the interaction noise of the jet blowing on the flaps. The latter noise-source area is the most critical and the main subject dicussed. Characteristics of lower surface blown and upper surface blown systems are described, including noise spectra, directivity, jet velocity characteristics, aircraft geometric variation effects, and aircraft forward speed effects. Noise reduction concepts are described, including slowing down the jet flow field by devices and engine cycle modifications, structural geometry and shielding modifications, local flow field modifications of the passive and active type, and the absorption of noise. It is concluded that, while there has been considerable progress in the past several years, low noise characteristics in blown flap aircraft must be largely built in by better application of low noise principles during the design.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145086 , Congr. of ICAS; Oct 03, 1976 - Oct 08, 1976; Ottawa
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Aerodynamic performance of two variable-pitch fan stages (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: NASA-Lewis Research Center is investigating a variety of fan stages applicable for short-haul aircraft. These low-pressure-ratio low-speed fan stages may require variable-pitch rotor blades to provide optimum performance for the varied flight demands and for thrust reversal on landing. A number of the aerodynamic and structural compromises relating to variable-pitch rotor blades are discussed. The aerodynamic performance of two variable-pitch fan stages operated at several rotor-blade setting angles is evaluated for both forward- and reverse-flow application. Detailed radial surveys are presented for both forward and reverse flow.
    Keywords: AERODYNAMICS
    Type: ICAS PAPER 76-41 , Congress; Oct 03, 1976 - Oct 08, 1976; Ottawa; Canada
    Format: text
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    NASA TECHNICAL REPORTS
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