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  • 1
    Publication Date: 2006-04-20
    Description: Cross wind effects on trajectory and cross section of turbulent jet
    Keywords: AERODYNAMICS
    Type: NASA, WASHINGTON ANALYSIS OF A JET IN A SUBSONIC CROSSWIND 1969; P 141-164
    Format: text
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  • 2
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 182-189
    Format: text
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  • 3
    Publication Date: 2019-06-28
    Description: The experimental approach presented here offers a nonintrusive, qualitative and quantitative evaluation of full field flow patterns applicable in various geometries in a variety of fluids. This Full Flow Field Tracking (FFFT) Particle Image Velocimetry (PIV) technique, by means of particle tracers illuminated by a laser light sheet, offers an alternative to Laser Doppler Velocimetry (LDV), and intrusive systems such as Hot Wire/Film Anemometry. The method makes obtainable the flow patterns, and allows quantitative determination of the velocities, accelerations, and mass flows of an entire flow field. The method uses a computer based digitizing system attached through an imaging board to a low luminosity camera. A customized optical train allows the system to become a long distance microscope (LDM), allowing magnifications of areas of interest ranging up to 100 times. Presented in addition to the method itself, are studies in which the flow patterns and velocities were observed and evaluated in three distinct geometries, with three different working fluids. The first study involved pressure and flow analysis of a brush seal in oil. The next application involved studying the velocity and flow patterns in a cowl lip cooling passage of an air breathing aircraft engine using water as the working fluid. Finally, the method was extended to a study in air to examine the flows in a staggered pin arrangement located on one side of a branched duct.
    Keywords: AERODYNAMICS
    Type: NASA-CR-195300 , E-8692 , NAS 1.26:195300
    Format: application/pdf
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  • 4
    Publication Date: 2019-06-28
    Description: Simulations of the near wake flowfield behind three aerobrakes have been implemented with Program LAURA, an algorithm for obtaining the numerical solution to the governing equations for three-dimensional, viscous, hypersonic flows in chemical and thermal nonequilibrium. Emphasis is placed on understanding the conditons which are likely to cause the shear layer to impinge on a payload positioned behind the aerobrake. A linear relationship between shear layer deflection angle and angle of attack (or lift-to-drag ratio) has been identified in several ground based tests. A similar relation appears in the numerical simulations, though there is some evidence that deflection angels may increase somewhat due to the effects of gas chemistry. Shear layer impingement can raise local heating levels a factor of 10 higher than levels present without impingement. Payload heating levels near impingement points are a larger percentage of stagnation point heating levels at higher altitudes and peak payload heating levels are likely to occur earlier in the trajectory than peak heating on the forebody stagnation point.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-1371
    Format: text
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