Author: I. A. Johnsen
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 19
Book Description
A radial-inlet impeller based on two-dimensional-flow theory has been investigated in a research program to establish correlation between flow theory and impeller performance. The simplifying assumptions of an infinite number of blades and an incompressible fluid were made for this impeller design. The blade shape was determined by imposing a predetermined vortex distribution that was chosen to relieve the loading in the critical regions of the impeller passage. The performance of the impeller was experimentally obtained in a variable-component test unit in conjunction with a vaneless diffuser of NACA design. An analysis of flow characteristics in the compressor, using static-pressure experimental data and the assumption of an infinite number of blades, indicated that the peak impeller efficiency was high and that the low over-all efficiency could be largely attributed to losses in the vaneless diffuser. The entrance section of the impeller and the passage in the region of the impeller-blade tip operated ineffectively even at the point of peak over-all efficiency. The entrance loss, whcih became very large at high flow, was the principal factor determining the form of the compressor-performance curve. The method developed for determining compressor performance from static-pressure measurements is limited to radial-inlet-type impellers in which flow is essentially two dimensional.
Performance of a Radial-inlet Impeller Designed on the Basis of Two-dimensional-flow Theory for an Infinite Number of Blades
Author: I. A. Johnsen
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 19
Book Description
A radial-inlet impeller based on two-dimensional-flow theory has been investigated in a research program to establish correlation between flow theory and impeller performance. The simplifying assumptions of an infinite number of blades and an incompressible fluid were made for this impeller design. The blade shape was determined by imposing a predetermined vortex distribution that was chosen to relieve the loading in the critical regions of the impeller passage. The performance of the impeller was experimentally obtained in a variable-component test unit in conjunction with a vaneless diffuser of NACA design. An analysis of flow characteristics in the compressor, using static-pressure experimental data and the assumption of an infinite number of blades, indicated that the peak impeller efficiency was high and that the low over-all efficiency could be largely attributed to losses in the vaneless diffuser. The entrance section of the impeller and the passage in the region of the impeller-blade tip operated ineffectively even at the point of peak over-all efficiency. The entrance loss, whcih became very large at high flow, was the principal factor determining the form of the compressor-performance curve. The method developed for determining compressor performance from static-pressure measurements is limited to radial-inlet-type impellers in which flow is essentially two dimensional.
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 19
Book Description
A radial-inlet impeller based on two-dimensional-flow theory has been investigated in a research program to establish correlation between flow theory and impeller performance. The simplifying assumptions of an infinite number of blades and an incompressible fluid were made for this impeller design. The blade shape was determined by imposing a predetermined vortex distribution that was chosen to relieve the loading in the critical regions of the impeller passage. The performance of the impeller was experimentally obtained in a variable-component test unit in conjunction with a vaneless diffuser of NACA design. An analysis of flow characteristics in the compressor, using static-pressure experimental data and the assumption of an infinite number of blades, indicated that the peak impeller efficiency was high and that the low over-all efficiency could be largely attributed to losses in the vaneless diffuser. The entrance section of the impeller and the passage in the region of the impeller-blade tip operated ineffectively even at the point of peak over-all efficiency. The entrance loss, whcih became very large at high flow, was the principal factor determining the form of the compressor-performance curve. The method developed for determining compressor performance from static-pressure measurements is limited to radial-inlet-type impellers in which flow is essentially two dimensional.
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 914
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 914
Book Description
The Flow and Force Characteristics of Supersonic Airfoils at High Subsonic Speeds
Author: W. F. Lindsey
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 524
Book Description
An investigation has been conducted at subsonic Mach numbers in the Langley rectangular high-speed tunnel on five supersonic airfoils and, for comparison, on two subsonic airfoils. Two-dimensional data were obtained by pressure measurements and schlieren photographs at angles of attack from 0 degrees to 4 degrees for Mach numbers between 0.30 and 0.90 for these 6-percent-thick symmetrical airfoils.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 524
Book Description
An investigation has been conducted at subsonic Mach numbers in the Langley rectangular high-speed tunnel on five supersonic airfoils and, for comparison, on two subsonic airfoils. Two-dimensional data were obtained by pressure measurements and schlieren photographs at angles of attack from 0 degrees to 4 degrees for Mach numbers between 0.30 and 0.90 for these 6-percent-thick symmetrical airfoils.
Index of NACA Technical Publications
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 616
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 616
Book Description
Material Presented at the Conference on Compressor Research at Aircraft Engine Research Laboratory on September 11, 1946
Author:
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 226
Book Description
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 226
Book Description
NACA Research Memorandum
Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 46
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 46
Book Description
A Selected Listing of NASA Scientific and Technical Reports for ...
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 664
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 664
Book Description
Report
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 620
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 620
Book Description
List of Technical Notes, 1947-1953
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 162
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 162
Book Description
Experimental Investigation of Heat Transfer Through Laminar and Turbulent Boundary Layers on a Cooled Flat Plate at a Mach Number of 2.4
Author: Ellis G. Slack
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 734
Book Description
Wind-tunnel tests of the heat-transfer characteristics for laminar and turbulent boundary layers on a cooled flat plate were conducted at a Mach number of 2.4. Data were obtained for a Reynolds number range of 150.000 to 3,000.000 and for a surface-temperature range of -40 degrees F to 45 degrees F with recovery temperature of the order of 65 degrees F. The temperature-recovery factors agreed well with previous flat-plate reslts. The heat-transfer results were obtained with negative temperature gradients along the surface and, when related to the constant-surface-temperature case, were, in general, in good agreement with theory.
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 734
Book Description
Wind-tunnel tests of the heat-transfer characteristics for laminar and turbulent boundary layers on a cooled flat plate were conducted at a Mach number of 2.4. Data were obtained for a Reynolds number range of 150.000 to 3,000.000 and for a surface-temperature range of -40 degrees F to 45 degrees F with recovery temperature of the order of 65 degrees F. The temperature-recovery factors agreed well with previous flat-plate reslts. The heat-transfer results were obtained with negative temperature gradients along the surface and, when related to the constant-surface-temperature case, were, in general, in good agreement with theory.