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  • AERODYNAMICS  (128)
  • 1980-1984
  • 1970-1974  (128)
  • 1974  (59)
  • 1972  (69)
  • 1
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    Flap noise generation and control (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The characteristics of aerodynamic noise generated by the interaction of an airstream with a flap surface are discussed. The location and behavior of various noise sources were investigated to determine optimal quieting techniques. A schematic diagram of the jet-flap concepts being considered for integrated-powered-lift systems for short takeoff aircraft is shown. Each of the concepts has in common high velocity turbulent air flowing over relatively rigid surfaces with resultant production of interaction noise. The nature, location, and control of noise sources which involve the interactions of air flows with airfoil surfaces are examined.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 413-426
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Acoustic characteristics of large-scale STOL models at forward speed (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Wind-tunnel investigations of the acoustic characteristics of the externally blown jet flap (EBF) and augmentor wing STOL concepts are discussed. The large-scale EBF model was equipped with a triple-slotted flap blown by four JT15D turbofan engines with circular, coannular exhaust nozzles. The large-scale augmentor wing model was equipped with an unlined augmentor blown by a slot primary nozzle. The effects of airspeed and angle of attack on the acoustics of the EBF were small. Flap deflection had a greater effect on the acoustics of the augmentor wing than did airspeed. The total sound power was also significantly higher for landing indicating that turning in the augmentor generated acoustic energy. Airspeed produced a small aft shift in acoustic directivity with no significant change in the peak perceived noise levels or sound power levels. Small-scale research of the acoustics for the augmentor wing has shown that by blowing an acoustically treated augmentor with a lobed primary nozzle, the 95-PNdb noise level goal can be achieved or surpassed.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 443-454
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Simulator evaluation of the flying qualities of externally blown flap and augmentor wing transport configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Concurrent simulations of powered-lift STOL transport aircraft having either an externally blown flap configuration or an augmentor wing configuration were conducted. The following types of simulators of varying sophistication were used: (1) a simple fixed-base simulation with a simple visual display, (2) a more complex fixed-base simulation using a realistic transport cockpit and a high-quality visual display, and (3) a six-degree-of-freedom motion simulator that had a realistic transport cockpit and a sophisticated visual display. The unaugmented flying qualities determined from these simulations were rated as unacceptable for both the externally blown flap and augmentor wing configurations. The longitudinal, lateral-directional, and single-engine-failure characteristics were rated satisfactory with extensive augmentation, including pitch and roll command systems, flight-path (or speed) augmentation, turn coordination, and effective yaw damping. However, the flare and landing characteristics from any approach glide-path angle in excess of 4 deg were rated as unsatisfactory but acceptable.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 157-800
    Format: text
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  • 4
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    Aerodynamic characteristics of a swept augmentor wing (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: A brief outline of augmentor wing research sponsored by Ames Research Center is presented and is followed by a discussion of large-scale wind-tunnel test results for a swept augmentor wing configuration. The results showed that the augmentor wing could be applied to high-speed swept wing designs with little adverse effect on either the basic performance of the augmentor or the longitudinal characteristics, including maximum lift and stall. Three lateral control devices were shown to be effective and ground effect was measured for several complete aircraft configurations.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 71-86
    Format: text
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  • 5
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    An invariant second-order closure model of the compressible turbulent boundary layer on a flat plate (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The development of an invariant model designed expressly for the computation of shear flows is discussed. The model for incompressible layers seeks a second-order closure of the equations for the mean and fluctuating fields. The development of a method for computing the behavior of shear layers in compressible forces is described. The complexity of the analysis is restrained by limiting the consideration to a flat plate boundary layer where the mean pressure can be taken to be constant.
    Keywords: AERODYNAMICS
    Type: NASA-CR-128172
    Format: application/pdf
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  • 6
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    Flight testing techniques for the evaluation of light aircraft stability derivatives: A review and analysis (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Techniques quoted in the literature for the extraction of stability derivative information from flight test records are reviewed. A recent technique developed at NASA's Langley Research Center was regarded as the most productive yet developed. Results of tests of the sensitivity of this procedure to various types of data noise and to the accuracy of the estimated values of the derivatives are reported. Computer programs for providing these initial estimates are given. The literature review also includes a discussion of flight test measuring techniques, instrumentation, and piloting techniques.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2016
    Format: application/pdf
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  • 7
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    Performance of a 1380-foot-per-second-tip-speed axial-flow compressor rotor with a blade tip solidity of 1.3 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Aerodynamic design parameters are presented along the overall and blade element performance, of an axial flow compressor rotor designed to study the effects of blade solidity on efficiency and stall margin. At design speed the peak efficiency was 0.844 and occurred at an equivalent weight flow of 63.5 lb/sec with a total pressure ratio of 1.801. Design efficiency, pressure ratio, and weight flow 0.814, 1.65, and 65.3(41.1 lb/sec/sq ft of annulus area), respectively. Stall margin for design speed was 6.4 percent based on the weight flow and pressure ratio values at peak efficiency and just prior to stall.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2448 , E-6503
    Format: application/pdf
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  • 8
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    Performance of 1380-foot-per-second tip-speed axial-flow compressor rotor with blade tip solidity of 1.1 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aerodynamic design parameters are presented along with the overall and blade element performance, of an axial-flow compressor rotor designed to study the effects of blade solidity on efficiency and stall margin. At design speed the peak efficiency was 0.853 and occured at an equivalent weight flow of 65.7lb/sec. The total pressure ratio was 1.68. Design efficiency, weight flow, pressure ratio, and temperature ratio were 0.822, 65.3, 1.65, and 1.187, respectively. Stall margin for design speed was 14 percent based on the weight flows and pressure ratios at peak efficiency and just prior to stall.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2449 , E-6686
    Format: application/pdf
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  • 9
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    Aerodynamic characteristics of an NASA supercritical-wing research airplane model with and without fuselage area-rule additions at Mach 0.25 to 1.00 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Transonic pressure tunnel tests at Mach numbers from 0.25 to 1.00 were performed to determine the effects of area-rule additions to the sides of the fuselage on the aerodynamic characteristics of a 0.087 scale model of an NASA supercritical-wing research airplane. Presented are the longitudinal aerodynamic force and moment characteristics for horizontal-tail deflection angles of -2.5 deg and -5 deg with the side fuselage area-rule additions on and off the model. The effects of the side fuselage area-rule additions on selected wing and fuselage pressure distributions at near-cruise conditions are also presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2633 , L-8422
    Format: application/pdf
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  • 10
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    Tabulated pressure measurements of a NASA supercritical-wing research airplane model with and without fuselage area-rule additions at Mach 0.25 to 1.00 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Basic pressure measurements were made on a 0.087-scale model of a supercritical wing research airplane in the Langley 8 foot transonic pressure tunnel at Mach numbers from 0.25 to 1.00 to determine the effects on the local aerodynamic loads over the wing and rear fuselage of area-rule additions to the sides of the fuselage. In addition, pressure measurements over the surface of the area-rule additions themselves were obtained at angles of sideslip of approximately - 5 deg, 0 deg, and 5 deg to aid in the structural design of the additions. Except for representative figures, results are presented in tabular form without analysis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2634 , L-8443
    Format: application/pdf
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