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  • AERODYNAMICS  (381)
  • Fisheries
  • 2020-2023
  • 1975-1979  (381)
  • 1950-1954
  • 1978  (381)
  • 1
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    Practical calculation of laminar and turbulent bled-off boundary layers (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Bleed-off of boundary layer material is shown to be an effective means for reducing drag by conserving the laminar boundary layer and preventing separation of the turbulent boundary layer. The case in which the two effects of bleed-off overlap is examined. Empirical methods are extended to the case of bleed-off. Laminar and turbulent boundary layers are treated simultaneously and the approximation differential equations are solved without an uncertain error. The case without bleed-off is also treated.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75328
    Format: application/pdf
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  • 2
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    Effect of the properties of a porous coating on boundary layer stability (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Drawing off gas from the boundary layer is a well-known method for increasing the stability of boundary layers. The increase in stability is primarily connected with a change in the velocity profile form in the case of suction. On the basis of the assumption that the velocity perturbations on a porous slate do not equal zero, the influence of the properties of a permeable surface upon the boundary layer stability were studied.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75235
    Format: application/pdf
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  • 3
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    Experimental studies on the influence of the degree of turbulence and of a turbulence thread on the compressible subsonic flow through flat compressor cascades (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The measurements revealed that at low Reynolds numbers the profile loss is considerably reduced both by the increased degree of turbulence and by a turbulence thread, while it is somewhat increased at high Reynolds numbers, and that a profile loss reduction is connected with an increase in deflection and in pressure shift. The turbulence generator is most effective on the one hand in the middle of the operating range of the cascades, and on the other at very high Mach numbers together with a large angle of incidence.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75276
    Format: application/pdf
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  • 4
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    A finite volume method for calculating transonic potential flow around wings from the pressure minimum integral (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Analysis of the pressure minimum integral in the calculation of three-dimensional potential flow around wings makes it possible to use non-rectangular mesh networks for distributing the three-dimensional potential into discrete points. The method is comparatively easily expanded to the treatment of realistic airplane configurations. Shock-pressure affected pressure distributions on any wings are determined with accuracy using this method.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75324
    Format: application/pdf
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  • 5
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    Measurement of the turbulence intensity behind a two-dimensional cascade and in a three-stage axial blower (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Turbulence intensity (Tu) measurements were made in two-dimensional and rotating cascades of blades in a low-speed cascade wind tunnel using hot-wire probes as sensors. The local Tu at Re = 1.6x100000 was determined in the wake zone behind a two-dimensional cascade. Then the values were recomputed for a rotating cascade, giving a mean turbulence intensity of 6.5% at 1/10 chord downstream and 2.9% at one chord. Fans were used for measurements on the rotating cascade. Re was equal to 7x100000. Frequency analysis was employed to separate the actual Tu of the entry flow from the effects caused by interaction with the rotor blades, showing that the true Tu increased from a few tenths of a percent to 6.6% in the 1st rotor, and from 7.2 to 9.3% in the 2d rotor. The Tu behind the 3d rotor was equal to 8.9%.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75275
    Format: application/pdf
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  • 6
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    Methods and results of boundary layer measurements on a glider (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Boundary layer measurements were carried out on a glider under natural conditions. Two effects are investigated: the effect of inconstancy of the development of static pressure within the boundary layer and the effect of the negative pressure difference in a sublaminar boundary layer. The results obtained by means of an ion probe in parallel connection confirm those results obtained by means of a pressure probe. Additional effects which have occurred during these measurements are briefly dealt with.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75294
    Format: application/pdf
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  • 7
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    Summary of experimentally determined facts concerning the behavior of the boundary layer and performance of boundary layer measurements (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A summary report of boundary layer studies is presented. Preliminary results of experimental measurements show that: (1) A very thin layer (approximately 0.4 mm) of the boundary layer seems to be accelerated; (2) the static pressure of the outer flow does not remain exactly constant through the boundary layer; and (3) an oncoming boundary layer which is already turbulent at the suction point can again become laminar behind this point without being completely sucked off.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75270
    Format: application/pdf
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  • 8
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    Airfoil profile in a nonuniform flow (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A theory of airfoil section past two dimensional nonuniform flow is developed. The theory is based on representation of airfoil section by vortex and source distributions and it can be used for calculation of aircraft wings in homogeneous and inhomogeneous flow, as well as for calculation of straight and radial blade and vane-cascades.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75272
    Format: application/pdf
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  • 9
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    Transonic flow past an airfoil with condensation (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: In connection with investigations conducted to determine the influence of water vapor on experiments in wind tunnels, the question arose as to what changes due to vapor condensation might be expected in airfoil measurements. Density measurements on circular-arc airfoils aided by an interferometer in choked tunnels with parallel walls show that increasing humidity produces increasing changes in the flow field. The flow becomes nonstationary at high humidity. At the airfoil, however, the influence of the condensation is only felt, inasmuch as the shock bounding the local supersonic region moves upstream with increasing humidity while its intensity decreases. The density distribution upstream of the shock remains unchanged. Even if the flow becomes nonstationary in the vicinity of the airfoil, no changes occur at the airfoil.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75201
    Format: application/pdf
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  • 10
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    Measurement of unsteady pressures in rotating systems (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The principles of the experimental determination of unsteady periodic pressure distributions in rotating systems are reported. An indirect method is discussed, and the effects of the centrifugal force and the transmission behavior of the pressure measurement circuit were outlined. The required correction procedures are described and experimentally implemented in a test bench. Results show that the indirect method is suited to the measurement of unsteady nonharmonic pressure distributions in rotating systems.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75445 , DLR-FB-77-34
    Format: application/pdf
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