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  • 1
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    Overview of the Langley subsonic research effort on SCR configuration (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Recent advances achieved in the subsonic aerodynamics of low aspect ratio, highly swept wing designs are summarized. The most significant of these advances was the development of leading edge deflection concepts which effectively reduce leading edge flow separation. The improved flow attachment results in substantial improvements in low speed performance, significant delay of longitudinal pitch up, increased trailing edge flap effectiveness, and increased lateral control capability. Various additional theoretical and/or experimental studies are considered which, in conjunction with the leading edge deflection studies, form the basis for future subsonic research effort.
    Keywords: AERONAUTICS (GENERAL)
    Type: Supersonic Cruise Res. 1979, Pt. 1; p 13-33
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Directivity and trends of noise generated by a propeller in a wake (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental study of the effects on far-field propeller noise of a pylon wake interaction was conducted with a scale model of a single-rotation propeller in a low-speed anechoic wind tunnel. A detailed mapping of the noise directivity was obtained at 10 test conditions covering a wide range of propeller power landings at several subsonic tip speeds. Two types of noise penalties were investigated-pulser and spacing. The pusher noise penalty is the difference in the average overall sound pressure level, OASPL, for pusher and tractor installations. (In a pusher installation, the propeller disk is downstream of a pylon or another aerodynamic surface.) The spacing noise penalty is the difference in the average OASPL for different distances between the pylon trailing edge and the propeller. The variations of these noise penalties with axial, or flyover, angle theta and circumferential angle phi are presented, and the trends in these noise penalties with tip Mach number and power loading are given for selected values of theta and phi. The circumferential directivity of the noise from a pusher installation showed that the addition noise due to the interaction of the pylon wake with the propeller had a broad peak over a wide range of circumferential angles approximately perpendicular to the pylon with a sharp minimum 90 deg. to the pylon for the majority of cases tested. The variation of the pusher noise penalty with theta had a minimum occurring near the propeller plane and maximum values of as much as 20 dB occurring toward the propeller axes. The magnitude of the pusher noise penalty generally decreased as propeller tip Mach number or power loading was increased.
    Keywords: ACOUSTICS
    Type: NASA-TP-2609 , L-16131 , NAS 1.60:2609
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Reynolds number effects on pressure loss and turbulence characteristics of four tube-bundle heat exchangers (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The aerodynamic characteristics of pressure loss and turbulence on four tube-bundle configurations representing heat-exchanger geometries with nominally the same heat capacity were measured as a function of Reynolds numbers from about 4000 to 400,000 based on tube hydraulic diameter. Two configurations had elliptical tubes, the other two had round tubes, and all four had plate fins. The elliptical-tube configurations had lower pressure loss and turbulence characteristics than the round-tube configurations over the entire Reynolds number range.
    Keywords: AERODYNAMICS
    Type: NASA-TM-85807 , L-15721 , NAS 1.15:85807
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Description of 0.186-scale model of high-speed duct of national transonic facility (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The National Transonic Facility (NTF) is a pressurized cryogenic wind tunnel with a 2.5 m square test section. A 0.186-scale model of the NTF was used to simulate the aerodynamic performance of the components of the high-speed duct of the NTF. These components consist of a wide-angle diffuser, settling chamber, contraction section, test section, model support section, and high-speed diffuser. The geometry of the model tunnel, referred to as the diffuser flow apparatus is described, and some of its operating characteristics are presented.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-TM-81949 , L-13523
    Format: application/pdf
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