3 edition of Development of a three-dimensional supersonic inlet flow analysis found in the catalog.
January 1980--Cover.Includes bibliographical references.
|Statement||National Aeronautics and Space Administration, Scientific and Technical Information Office|
|Publishers||National Aeronautics and Space Administration, Scientific and Technical Information Office|
|The Physical Object|
|Pagination||xvi, 99 p. :|
|Number of Pages||55|
|2||NASA contractor report -- NASA CR-3218.|
|3||NASA contractor report -- 3218.|
nodata File Size: 3MB.
When calculating the velocity, the motion of the fluid is neglected.
One- dimensional flow; boundary layer is represented only by its average effect on flow properties. For the Mach 7 configurations maximum back pressure ratios of approximately 120 were measured, which is about 4 times the nominal operating pressure ratio. Because of this, only a little pressure rise is recorded, although it is expected to be of the same magnitude than in the other cases.
Since it is based on a 24-hour dietary recall, this variable may be particularly susceptible to measurement error induced by recall bias. See also: ISABE-93-7104 Nobel, T. Engine cooling system uses the relatively cool air from the compression system that bypasses the combustor via air system flow paths to cool the turbine nozzle guide vanes and blades to ensure acceptable metal temperatures at elevated gas temperatures.
In addition to the parameter studies, a more rigorous approach to the optimal design and control has been taken. In the bottom half, the flow structure is very much influenced by the shock from the fixed part of the cowl, and thus the influence of the lip position is not as distinct.
Also AIAA Paper 2010-0032 and NASA TM-2010-216744, July 2010. In this model, viscous effects in blade passages can also be calculated directly, which include the exchange of momentum between fluids and detailed viscous flow close to walls.
A symmetric supersonic flow pattern was observed at both supercritical and critical operating conditions of the present Y-shaped DSI. Compared to external compression, this method has, in general, less of an entropy increase, but the overall length required for the shock system is greater. The distribution of y to be used in the model, in this package, must be binomial, Gaussian, or Poisson.
The 3-D combustion processes become more complex compared to those identified in the premixed study due to the additional shock structures introduced from the injection method and associated mixing processes. Capabilities highlighted in this paper include the design and analysis of streamline-traced external-compression inlets, modeling of Development of a three-dimensional supersonic inlet flow analysis bleed, and the design and analysis of mixed-compression inlets.
This type of inlet was extensively examined by Holland both computationally and experimentally [8, 9]. : Computational parametric study of sidewall-compression scramjet inlet performance at Mach 10. Space is composed of three orthogonal dimensions, and time is represented as a fourth dimension, perpendicular to each of the spatial axes.
Studies have also been made concerning the choices that need to be made in the thermal boundary conditions to optimize the vapor transport from the source and to establish uniform ow at the surface of the substrate .
The trend towards ultra compact thermal power generation, is constrained by the unavailability of fluid-machinery adequate for supersonic flow conditions.
Accepted : 13 February 2016• Show more 9 With the development of related disciplines such as aerodynamic and materials science, the single stage pressure ratio of centrifugal compressor continues to rise and the research of internal flow analysis becomes more.
Due to the location of the shock waves, very long ramps are necessary to achieve the required compression ratios.
A model that combines a short-range ob- stacle and a long-range obstacle is shown to match experimental measure- ments over a wide range of temperatures and grain sizes.