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  • FLUID MECHANICS AND HEAT TRANSFER  (218)
  • Aircraft Stability and Control
  • GENERAL
  • 1980-1984  (229)
  • 1955-1959  (23)
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  • 11
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    Monodisperse atomizers for agricultural aviation applications (1980)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Conceptual designs of two monodisperse spray nozzles are described and the rationale used in each design is discussed. The nozzles were designed to eliminate present problems in agricultural aviation applications, such as ineffective plant coverage, drift due to small droplets present in the spray being dispersed, and nonuniform swath coverages. Monodisperse atomization techniques are reviewed and a synopsis of the information obtained concerning agricultural aviation spray applications is presented.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NASA-CR-159777
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 12
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    Analytical modeling of operating characteristics of premixing-prevaporizing fuel-air mixing passages. Volume 2: User's manual (1982)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A user's manual describing the operation of three computer codes (ADD code, PTRAK code, and VAPDIF code) is presented. The general features of the computer codes, the input/output formats, run streams, and sample input cases are described.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NASA-CR-167990-VOL-2 , NAS 1.26:167990-V0L-2 , R82-915362-40-VOL-2
    Format: application/pdf
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  • 13
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    Computation of transonic viscous-inviscid interacting flow (1982)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Transonic viscous-inviscid interaction is considered using the Euler and inverse compressible turbulent boundary-layer equations. Certain improvements in the inverse boundary-layer method are mentioned, along with experiences in using various Runge-Kutta schemes to solve the Euler equations. Numerical conditions imposed on the Euler equations at a surface for viscous-inviscid interaction using the method of equivalent sources are developed, and numerical solutions are presented and compared with experimental data to illustrate essential points.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NASA-TM-85203 , NAS 1.15:85203
    Format: application/pdf
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  • 14
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    Analytical modeling of operating characteristics of premixing-prevaporizing fuel-air mixing passages. Volume 1: Analysis and results (1982)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A model for predicting the distribution of liquid fuel droplets and fuel vapor in premixing-prevaporizing fuel-air mixing passages of the direct injection type is reported. This model consists of three computer programs; a calculation of the two dimensional or axisymmetric air flow field neglecting the effects of fuel; a calculation of the three dimensional fuel droplet trajectories and evaporation rates in a known, moving air flow; a calculation of fuel vapor diffusing into a moving three dimensional air flow with source terms dependent on the droplet evaporation rates. The fuel droplets are treated as individual particle classes each satisfying Newton's law, a heat transfer, and a mass transfer equation. This fuel droplet model treats multicomponent fuels and incorporates the physics required for the treatment of elastic droplet collisions, droplet shattering, droplet coalescence and droplet wall interactions. The vapor diffusion calculation treats three dimensional, gas phase, turbulent diffusion processes. The analysis includes a model for the autoignition of the fuel air mixture based upon the rate of formation of an important intermediate chemical species during the preignition period.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NASA-CR-167990-VOL-1 , NAS 1.26:167990-VOL-1 , R82-915362-40-VOL-1
    Format: application/pdf
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  • 15
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    Analysis of active control by surface heating (1984)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The excitation of boundary-layer disturbances by active, localized periodic heating of the flow surfaces is investigated analytically. A triple-deck model is used in the matched-asymptotics approach, and the incompressible case with small temperature variations, a linearized 3-deck problem, is considered. This case corresponds to the experimental (water-tunnel) conditions of Liepmann et al. (1982), who demonstrated that the induced disturbances can be used to enhance or suppress the Tollmien-Schlichting waves. Here the energy equation is uncoupled from the momentum and continuity equations to permit definition of the thermal-sublayer temperature profile by superposition of canonical solutions, which are presented in an appendix. A diagram of the 3-deck structure and graphs of calculated results are included.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: AIAA PAPER 84-0173
    Format: text
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  • 16
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    Application of thin-layer Navier-Stokes equations near maximum lift (1984)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The flowfield about a NACA 0012 airfoil at a Mach number of 0.3 and Reynolds number of 1 million is computed through an angle of attack range, up to 18 deg, corresponding to conditions up to and beyond the maximum lift coefficient. Results obtained using the compressible thin-layer Navier-Stokes equations are presented as well as results from the compressible Euler equations with and without a viscous coupling procedure. The applicability of each code is assessed and many thin-layer Navier-Stokes benchmark solutions are obtained which can be used for comparison with other codes intended for use at high angles of attack. Reasonable agreement of the Navier-Stokes code with experiment and the viscous-inviscid interaction code is obtained at moderate angles of attack. An unsteady solution is obtained with the thin-layer Navier-Stokes code at the highest angle of attack considered. The maximum lift coefficient is overpredicted, however, in comparison to experimental data, which is attributed to the presence of a laminar separation bubble near the leading edge not modeled in the computations. Two comparisons with experimental data are also presented at a higher Mach number.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: AIAA PAPER 84-0049
    Format: text
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  • 17
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    Diffusive separation of binary mixtures of CO2-H2 in a sonic-orifice expansion (1983)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The separation of binary gas mixtures of carbon dioxide and hydrogen in sonic-orifice-generated free jets is investigated over a source Reynolds number range of 100 to 3000 using the well-known electron beam fluorescence technique. The lighter species, hydrogen, is chosen as the minor species in order to examine the extent of the validity of Sherman's first-order diffusive separation theory for large separation. The diffusive separation of mixtures containing approximately 2, 5, and 20 percent hydrogen in carbon dioxide is investigated by experimentally determining the relative number densities of the two species as a function of centerline axial distance within the free jets. Sherman's diffusive separation theory is applied to the jets using axial Mach number profiles which were a combination of experimental and analytical results for gamma = 1.40 expansions. The gamma = 1.40 expansion is shown to approximate the CO2-H2 expansion quite well, and the calculated separation agrees remarkably well with the experimentally determined values.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: AD-A140617 , AEDC-TR-83-60 , Physics of Fluids (ISSN 0031-9171); 26; Aug. 198
    Format: text
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  • 18
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    An analytical tool for simulating Large AMplitude Propellant Slosh (1981)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The development of a multiple-mass, nonlinear, finite-element analytical model - the Large AMplitude Propellant Slosh model (LAMPS) in two- and three-dimensional versions, is described. The model is used in predicting the forces on the Space Shuttle external tank caused by large amplitude motion of propellant fluid. Comparisons between measured propellant reorientation forces and those predicted by the LAMPS models are presented, and it is concluded that the model provides a cost effective, experimentally verified approach to a complicated nonlinear problem.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: AIAA PAPER 81-0500 , Conference on Structures, Structural Dynamics and Materials; Apr 06, 1981 - Apr 08, 1981; Atlanta, GA
    Format: text
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  • 19
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    Hybrid suction surface for turbulent boundary layer flow (1980)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A hybrid suction surface which combines favorable aspects of both uniformly porous and discrete opening suction surfaces has been evaluated experimentally for use with incompressible turbulent boundary layers. The surface consisted of an array of closely spaced slots aligned in the direction of the freestream flow. Direct drag and mean boundary layer velocity profile measurements showed that the slotted surface had nominally the same suction characteristics as a uniformly porous surface.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: Symposium on Viscous flow drag reduction; Nov 07, 1979 - Nov 08, 1979; Dallas, TX
    Format: text
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  • 20
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    Experimental results for a two-dimensional supersonic inlet used as a thrust deflecting nozzle (1984)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Nearly all supersonic V/STOL aircraft concepts are dependent on the thrust deflecting capability of a nozzle. In one unique concept, referred to as the reverse flow dual fan, not only is there a thrust deflecting nozzle for the fan and core engine exit flow, but because of the way the propulsion system operates during vertical takeoff and landing, the supersonic inlet is also used as a thrust deflecting nozzle. This paper presents results of an experimental study to evaluate the performance of a supersonic inlet used as a thrust deflecting nozzle for this reverse flow dual fan concept. Results are presented in terms of nozzle thrust coefficient and thrust vector angle for a number of inlet/nozzle configurations. Flow visualization and nozzle exit flow survey results are also shown.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NASA-TM-83439 , E-1737 , NAS 1.15:83439 , Joint Propulsion Conference; Jun 27, 1983 - Jun 29, 1983; Seattle, WA; United States
    Format: application/pdf
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