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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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  • 2
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    Effect of Subsonic Inlet Lip Geometry on Predicted Surface and Flow Mach Number Distributions (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of subsonic inlet lip geometry on predicted surface and flow Mach number distributions is illustrated. The theoretical results were obtained from incompressible potential flow calculations corrected for compressibility. The major emphasis of this investigation is on the low-speed (takeoff and landing) operating conditions. The low-speed results were obtained for a range of three geometric variables of interest: contraction ratio, defined as the ratio of highlight area to throat area; internal lip major - to minor-axis ratio; and internal lip shape. The low-speed results were obtained at both static conditions and a free-stream velocity of 42.6m/sec, with incidence angles ranging from 0 deg to 50 deg. The results indicate that of the three geometric variables considered, contraction ratio had the largest effect on the surface Mach number distributions. The effects of inlet diameter ratio and blunting of the external forebody on maximum external surface Mach numbers are illustrated at a cruise Mach number of 0.8.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7446 , E-7522
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  • 3
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    Theoretical surface velocity distributions on acoustic splitter geometries for an engine inlet (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The potential-flow velocity distributions on several splitter geometries in an engine inlet and their variation with different splitter leading-edge shapes and distances from the inlet highlight were analyzed. The velocity distributions on the inner and outer surfaces of the splitters are presented for low-speed and cruise conditions. At zero incidence angle, the splitter with the 4-to-1 elliptical leading edge had lower peak velocities and velocity gradients than the splitter with the 2-to-1 elliptical leading edge. The velocity gradients decreased as the distance from the inlet highlight to the splitter leading edge was increased. For a given distance, the peak velocity on the splitter inner surface increased with increasing inlet incidence angle. At an incidence angle of 50 deg, the velocity level and gradients on the inner surface of the splitter in the forward position were sufficiently severe to suggest local separation.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3114 , E-8001
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  • 4
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    Aerodynamic analysis of several high throat Mach number inlets for the quiet clean short-haul experimental engine (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of an analytical study to investigate internal and external surface Mach numbers on several inlet geometries for possible application to the nacelle of the Quiet Clean Short-Haul Experimental Engine (QCSEE) are presented. The effects of external forebody geometry and internal lip geometry were illustrated at both low-speed and cruise conditions. Boundary-layer analyses were performed on several geometries to determine if lip flow separation might exist. The results indicated that inner-surface Mach number level and gradient could be reduced with inlets at a 50 deg incidence angle by blunting the external forebody geometry. The external Mach numbers at cruise conditions indicated that a compromise in the external forebody bluntness might be required to satisfy both low-speed and cruise conditions. For a fixed value of bluntness parameter, no lip flow separation was indicated for the 1.46- and 1.57-area-contraction-ratio inlets at low-speed conditions. However, a lip separation condition was obtained with the 1.37-contraction-ratio inlet. The QCSEE nacelle design takeoff operating condition (incidence angle of 50 deg and free-stream Mach number of 0.12) resulted in higher peak surface Mach numbers than the design crosswind (incidence angle of 90 deg and free-stream Mach number of 0.05) or static condition.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3183 , E-8132
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  • 5
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    Potential flow solution for a STOL wing propulsion system (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Potential flow solution for STOL wing propulsion system presenting flow fields, pressure distribution, and lift coefficient for externally blown flap, high-lift configuration
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6394 , E-6132
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  • 6
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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
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  • 7
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    Sound radiation from a high speed axial flow fan due to the inlet turbulence quadrupole interaction (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A formula is obtained for the total acoustic power spectra radiated out the front of the fan as a function of frequency. The formula involves the design parameters of the fan as well as the statistical properties of the incident turbulence. Numerical results are calculated for values of the parameters in the range of interest for quiet fans tested at the Lewis Research Center. As in the dipole analysis, when the turbulence correlation lengths become equal to the interblade spacing, the predicted spectra exhibit peaks around the blade passing frequency and its harmonics. There has recently been considerable conjecture about whether the stretching of turbulent eddies as they enter a stationary fan could result in the inlet turbulence being the dominant source of pure tones from nontranslating fans. The results of the current analysis show that, unless the turbulent eddies become quite elongated, this noise source contributes predominantly to the broadband spectrum.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7667 , E-7741
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  • 8
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    Application of compressibility correction to calculation of flow in inlets. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An application of the compressibility correction developed by Lieblein and Stockman (1972) to the calculation of flow in axisymmetric inlets is described. The results with experimental data from wind tunnel model tests are compared. The configuration is a conventional subsonic inlet with a NACA series one external cowl shape and a two-to-one ellipse internal lip. It is shown that the compressibility correction gives a relatively good approximation to the internal compressible flow behavior, and thus should be useful in the design and analysis of engine nacelle inlets.
    Keywords: AERODYNAMICS
    Type: Application of compressibility correction to calculation of flow in inlets; Jul 01, 1973
    Format: text
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  • 9
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    Comparison of experimental and theoretical boundary-layer separation for inlets at incidence angle at low-speed conditions (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Comparisons between experimental and theoretical Mach number distributions and separation locations are presented for the internal surfaces of four different subsonic inlet geometries with exit diameters of 13.97 centimeters. The free stream Mach number was held constant at 0.127, the one-dimensional throat Mach number ranged from 0.49 to 0.71, and the incidence angle ranged from 0 deg to 50 deg. Generally good agreement was found between the theoretical and experimental surface Mach number distributions as long as no flow separation existed. At high incidence angles, where separation was obvious in the experimental data, the theory predicted separation on the lip. At lower incidence angles, the theoretical results indicated diffuser separation which was not obvious from the experimental surface Mach number distributions. As incidence angle was varied from 0 deg to 50 deg, the predicted separation location shifted from the diffuser region to the inlet highlight. Relatively small total pressure losses were obtained when the predicted separation location was greater than 0.6 of the distance between the highlight and the diffuser exit.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3194 , E-8182
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  • 10
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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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