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  • 1
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    A Comparison of the Aerodynamic Characteristics of Eight Sailwing Airfoil Sections (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The operational characteristics of sailwings are discussed with emphasis placed on the importance of the trailing edge cable tension. The three dimensional aerodynamic characteristics were obtained from wind tunnel tests, and the results compared to determine the magnitude of the aerodynamic penalties paid for various structural simplifications. For the sectional thickness ratios, it is concluded that, while the basic double-membraned sailwing has exceptional aerodynamic performance, even superior for some applications to the conventional hardwing, any notable deviation from this configuration results in an unacceptably large performance penalty.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center The Sci. and Technol. of Low Speed and Motorless Flight, Pt. 1; p 155-176
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Trailing edge flow conditions as a factor in airfoil design (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Some new developments relevant to the design of single-element airfoils using potential flow methods are presented. In particular, the role played by the non-dimensional trailing edge velocity in design is considered and the relationship between the specified value and the resulting airfoil geometry is explored. In addition, the ramifications of the unbounded trailing edge pressure gradients generally present in the potential flow solution of the flow over an airfoil are examined, and the conditions necessary to obtain a class of airfoils having finite trailing edge pressure gradients developed. The incorporation of these conditions into the inverse method of Eppler is presented and the modified scheme employed to generate a number of airfoils for consideration. The detailed viscous analysis of airfoils having finite trailing edge pressure gradients demonstrates a reduction in the strong inviscid-viscid interactions generally present near the trailing edge of an airfoil.
    Keywords: AERODYNAMICS
    Type: NASA-CR-173294 , NAS 1.26:173294 , AAE-84-1 , UILU-ENG-84-0501
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    The development of methods for predicting and measuring distribution patterns of aerial sprays (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A set of relationships used to scale small sized dispersion studies to full size results are experimentally verified and, with some qualifications, basic deposition patterns are presented. In the process of validating these scaling laws, the basic experimental techniques used in conducting such studies both with and without an operational propeller were developed. The procedures that evolved are outlined in some detail. The envelope of test conditions that can be accommodated in the Langley Vortex Research Facility, which were developed theoretically, are verified using a series of vortex trajectory experiments that help to define the limitations due to wall interference effects for models of different sizes.
    Keywords: AERONAUTICS (GENERAL)
    Type: NASA-CR-165652 , ARL-79-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    A class of airfoils having finite trailing edge pressure gradients (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Some new developments relevant to the design of single-element airfoils using potential flow methods are presented. In particular, the ramifications of the unbounded trailing edge pressure gradients generally present in the potential flow solution for the flow over an airfoil are examined, and the conditions necessary to obtain a class of airfoils having finite trailing edge pressure gradients developed. The incorporation of these conditions into the inverse method of Eppler for the design of low-speed airfoils is discussed, and designs generated using the modified scheme are presented for consideration. A detailed viscous analysis of one of these airfoils demonstrates a significant reduction in the strong inviscid-viscid interactions generally present near the trailing edge. These reductions offer the possibility of improved airfoil performance, as well as the possibility of improved accuracy in the methods of airfoil design and analysis.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-0206
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    The development of methods for predicting and measuring distribution patterns of aerial sprays (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The capability of conducting scale model experiments which involve the ejection of small particles into the wake of an aircraft close to the ground is developed. A set of relationships used to scale small-sized dispersion studies to full-size results are experimentally verified and, with some qualifications, basic deposition patterns are presented. In the process of validating these scaling laws, the basic experimental techniques used in conducting such studies, both with and without an operational propeller, were developed. The procedures that evolved are outlined. The envelope of test conditions that can be accommodated in the Langley Vortex Research Facility, which were developed theoretically, are verified using a series of vortex trajectory experiments that help to define the limitations due to wall interference effects for models of different sizes.
    Keywords: AERODYNAMICS
    Type: NASA-CR-158787 , ARL-79-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Scaling wake-particle interactions for aerial applications research (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The differential equation for the trajectory of a spherical particle injected into an aircraft wake was developed and the proper scaling relations extracted. After some simplification a convenient set of similarity parameters was established. Using these similarity parameters a scale model test program was designed and performed in the NASA Langley vortex research facility. The results of the tests demonstrated the validity of the similarity parameters in conducting scale model testing for aerial application research.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-1873 , Aircraft Systems Meeting; Aug 04, 1980 - Aug 06, 1980; Anaheim, CA
    Format: text
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