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  • 1
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    Condensation pressure drop of nonwetting mercury in a uniformly tapered tube in 1-g and zero-gravity environments (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Pressure drop of nonwetting condensing flow of mercury vapor in 1-g and zero gravity environments
    Keywords: FLUID MECHANICS
    Type: NASA-TN-D-3185
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Computer program for calculating laminar, transitional, and turbulent boundary layers for a compressible axisymmetric flow (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A finite-difference program is described for calculating the viscous compressible boundary layer flow over either planar or axisymmetric surfaces. The flow may be initially laminar and progress through a transitional zone to fully turbulent flow, or it may remain laminar, depending on the imposed boundary conditions, laws of viscosity, and numerical solution of the momentum and energy equations. The flow may also be forced into a turbulent flow at a chosen spot by the data input. The input may contain the factors of arbitrary Reynolds number, free-stream Mach number, free-stream turbulence, wall heating or cooling, longitudinal wall curvature, wall suction or blowing, and wall roughness. The solution may start from an initial Falkner-Skan similarity profile, an approximate equilibrium turbulent profile, or an initial arbitrary input profile.
    Keywords: FLUID MECHANICS
    Type: NASA-TN-D-7521 , E-7819
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Boundary-layer analysis of subsonic inlet diffuser geometries for engines nacelles (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Theoretical Mach number distributions and boundary-layer parameters are presented for subsonic nacelle inlet diffuser geometries with length to exit diameter ratios ranging from 0.4 to 1.6 and diffuser exit area to throat area ratios ranging from 1.1 to 2.0. The major portion of the study was done with a cubic diffuser contour with the inflection point at the midpoint of the diffuser, a diffuser throat Mach number of 0.6, and a free-stream Mach number of 0.12. Calculations were performed at both model (diffuser exit diameter, 30.5 cm) and full-scale (diffuser exit diameter, 183 cm) sizes. Separation limits were defined by establishing a separation boundary on plots of diffuser area ratio as a function of diffuser length to diameter ratio. The effects of diffuser contour, inlet lip geometry, and throat Mach number on the boundary-layer characteristics are illustrated. The major results of the study indicate that the separation boundary is shifted to greater area ratios by (1) increasing the diffuser length, (2) increasing the scale of the diffuser and, (3) moving the inflection point of the diffuser contour to or ahead of the midpoint of the diffuser.
    Keywords: FLUID MECHANICS
    Type: NASA-TN-D-7520 , E-7816
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Calculation procedures for potential and viscous flow solutions for engine inlets (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The method and basic elements of computer solutions for both potential flow and viscous flow calculations for engine inlets are described. The procedure is applicable to subsonic conventional (CTOL), short-haul (STOL), and vertical takeoff (VTOL) aircraft engine nacelles operating in a compressible viscous flow. The calculated results compare well with measured surface pressure distributions for a number of model inlets. The paper discusses the uses of the program in both the design and analysis of engine inlets, with several examples given for VTOL lift fans, acoustic splitters, and for STOL engine nacelles. Several test support applications are also given.
    Keywords: FLUID MECHANICS
    Type: NASA-TM-X-71457 , Intern. Gas Turbine Conf.; Mar 31, 1974 - Apr 04, 1974; Zurich; Switzerland
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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