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  • FLUID MECHANICS AND HEAT TRANSFER  (605)
  • 1995-1999  (36)
  • 1985-1989  (364)
  • 1975-1979  (205)
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  • 1
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    Hypersonic heat-transfer and transition correlations for a roughened shuttle orbiter (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The effect of roughness on the heat transfer distributions and the transition criteria for the windward pitch plane of the shuttle orbiter at an angle of attack of 30 deg was studied using data obtained in hypersonic wind tunnels. The heat transfer distributions and the transition locations for the roughened models were compared with the corresponding data for smooth models. The data were correlated using theoretical solutions for a nonsimilar, laminar boundary layer subject to two different flow field models for the orbiter.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: an. In Eng. Sci., Vol. 4; p 1615-1627
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Effects of multiple rows and noncircular orifices on dilution jet mixing (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 3; 219-226
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Laminar flow integration: Flight tests status and plans (1986)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Under the Aircraft Energy Efficiency - Laminar Flow Control Program, there are currently three flight test programs under way to address critical issues concerning laminar flow technology application to commercial transports. The Leading-Edge Flight Test (LEFT) with a JetStar aircraft is a cooperative effort with the Ames/Dryden Flight Research Facility to provide operational experience with candidate leading-edge systems representative of those that might be used on a future transport. In the Variable Sweep Transition Flight Experiment (VSTFE), also a cooperative effort between Langley and Ames/Dryden, basic transition data on an F-14 wing with variable sweep will be obtained to provide a data base for laminar flow wing design. Finally, under contract to the Boeing Company, the acoustic environment on the wing of a 757 aircraft will be measured and the influence of engine noise on laminar flow determined with a natural laminar flow glove on the wing. The status and plans for these programs are reported.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Langley Symposium on Aerodynamics, Volume 1; p 485-518
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Structure of unsteady flows at leading- and trailing-edges: Flow visualization and its interpretation (1987)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Unsteady two- and three-dimensional flow structure at leading and trailing edges of bodies can be characterized effectively using recently developed techniques for acquisition and interpretation of flow visualization. The techniques addressed here include: flow image/surface pressure correlations; 3-D reconstruction of flow structure from flow images; and interactive interpretation of flow images with theoretical simulations. These techniques can be employed in conjunction with: visual correlation and ensemble-averaging, both within a given image and between images; recognition of patterns from images; and estimates of velocity eigenfunctions from images.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AGARD, Aerodynamic and Related Hydrodynamic Studies Using Water Facilities; 13 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Heat transfer characteristics for inline and staggered arrays of circular jets with crossflow of spent air (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Heat transfer characteristics were measured for two dimensional arrays of jets impinging on a surface parallel to the jet orifice plate. The impinging flow was constrained to exit in a single direction along the channel formed by the jet plate and the heat transfer surface. Both mean Nusselt numbers and streamwise Nusselt number profiles are presented as a function of Reynolds number and geometric parameters. These are the streamwise and transverse hole spacings ranging from 5 to 10 and 4 to 8 jet orifice diameters, respectively; the channel height ranging from 1 to 6 diameters; and the hole pattern which includes both inline and staggered arrays. The results show that significant periodic variations occur in the streamwise Nusselt number profiles, persisting downstream for at least ten rows of jet holes. Channel height can have a significant effect on the chordwise profiles, smoothed across the periodic variations. For the smaller channel heights, Nusselt numbers first decrease and then increase downstream. Where significant differences exist, inline hole patterns provide better heat transfer than staggered ones. These and other effects of the geometric parameters are presented and discussed.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Gas turbine heat transfer 1978; Dec 10, 1978 - Dec 15, 1978; San Francisco, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Thermal response of integral, multicomponent composite thermal protection systems (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 23; 420-427
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Karhunen-Loeve expansion of Burgers' model of turbulence (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The properties of the Karhunen-Loeve expansion of a strongly inhomogeneous random process are examined with emphasis on applications to turbulent flow fields. The ability of the KL expansion to represent functions that have both slow and rapid variations in a relatively small number of expansion terms is tested on a one-dimensional model based on the forced Burgers' equation. The rate of the convergence of the expansion is evaluated, and its dependence on the Reynolds number is determined. It is shown that the KL eigenfunctions possess wall boundary layers attached to outer structures that are independent of the Reynolds number (at high Reynolds numbers). It is also shown that the spectrum of eigenvalues is broad at large Reynolds numbers, requiring many terms to represent higher-order derivatives of the function.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Physics of Fluids (ISSN 0031-9171); 31; 2573-258
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Drop dynamics in space (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Drop experiments proposed for Spacelab are discussed and an acoustic chamber utilizing the torques and forces produced by acoustic waves excited within the chamber is described. Its operation and how it is being tested for experiments is discussed.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: ESA Mater. Sci. in Space; p 405-419
    Format: text
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  • 9
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    An implicit-iterative solution of the heat conduction equation with a radiation boundary condition (1977)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: For the problem of predicting one-dimensional heat transfer between conducting and radiating mediums by an implicit finite difference method, four different formulations were used to approximate the surface radiation boundary condition while retaining an implicit formulation for the interior temperature nodes. These formulations are an explicit boundary condition, a linearized boundary condition, an iterative boundary condition, and a semi-iterative boundary method. The results of these methods in predicting surface temperature on the space shuttle orbiter thermal protection system model under a variety of heating rates were compared. The iterative technique caused the surface temperature to be bounded at each step. While the linearized and explicit methods were generally more efficient, the iterative and semi-iterative techniques provided a realistic surface temperature response without requiring step size control techniques.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: International Journal for Numerical Methods in Engineering; 11; 10, 1; 1977
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Sensitivity of mixing layers to three-dimensional forcing (1988)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: It is well known that turbulent mixing layers are dominated by large scale, fairly coherent structures, and that these structures are related to the stability characteristics of the flow. These facts have led researchers to attempt controlling such flows by selectively forcing certain unstable modes, which can in addition have the effect of suppressing other modes. Much of the work on controlling the mixing layer has relied on forcing 2-D instabilities. The results of forcing 3-D instabilities are addressed. The objectives of the work are twofold: to understand how a mixing layer responds to 3-D perturbations, and to test the validity of an amplitude expansion in predicting the mixing layer development. The amplitude expansion could be very useful in understanding and predicting the 3-D response of the flow to a variety of initial conditions.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Stanford Univ., Studying Turbulence Using Numerical Simulation Databases, 2. Proceedings of the 1988 Summer Program; p 91-116
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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