Hostname: page-component-7dd5485656-s6l46 Total loading time: 0 Render date: 2025-10-29T15:31:22.378Z Has data issue: false hasContentIssue false
  • English
  • Français

Boundary Layer Influence on the Performance of Submerged Intakes

Published online by Cambridge University Press:  04 July 2016

Katherine M. McCreath  and
A. J. Ward Smith
Katherine M. McCreath
Affiliation:
Engineering Sciences Data Unit, Royal Aeronautical Society
A. J. Ward Smith
Affiliation:
Engineering Sciences Data Unit, Royal Aeronautical Society
Get access Rights & Permissions [Opens in a new window]

Extract

Submerged intakes are widely used on aircraft as a means of supplying internal flow systems with ambient air. It is the purpose of this note to show by analysis of existing experimental data that the boundary layer at the location of the submerged intake can have an appreciable effect on its performance.

Information here relates to the NACA type of divergent submerged intake with a ramp angle, a, of 7° and an aspect ratio, w/d, of 4 because this particular combination of planform and geometry is now almost universally used.

Information

Type
Technical Notes
Information
The Aeronautical Journal , Volume 71 , Issue 680 , August 1967 , pp. 581 - 583
Copyright
Copyright © Royal Aeronautical Society 1967

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Article purchase

Temporarily unavailable

References

1.Mossman, E. A. and Randall, L. M. An Experimental Investigation of the Design Variables for NACA Submerged Duct Entrances. NACA RM No A7I30 (NACA/ TIB/1563), 1948.Google Scholar
2.Delany, N. K. An Investigation of Submerged Air In takes on a i-Scale Model of a Typical Fighter-Type Airplane. NACA RM No A8A20 (NACA/TIB/1822), 1948.Google Scholar
3.Martin, N. J. and Holzhauser, C. A. An Experimental Investigation at Large Scale of Several Configurations of an NACA Submerged Air Intake. NACA RM No A8F21 (NACA/TIB/1937), 1948.Google Scholar
4.Hall, C. F. and Frank, J. L. Ram-Recovery Characteristics of NACA Submerged Inlets at High Subsonic Speeds. NACA RM No A8I29 (NACA/TIB/1970), 1948.Google Scholar
5.Axelson, J. A. and Taylor, R. A. Preliminary Investigation of the Transonic Characteristics of an NACA Submerged Inlet. NACA RM A50C13 (NACA/TIB/2393), 1950.Google Scholar
6.Frank, J. L. Pressure-Distribution and Ram-Recovery Characteristics of NACA Submerged Inlets at High Subsonic Speeds. NACA RM A50E02 (NACA/TIB/2412), 1950.Google Scholar
7.Selna, J. and Schlaff, B. A. An Investigation of the Drag and Pressure Recovery of a Submerged Inlet and a Nose Inlet in the Transonic Flight Range with Free-Fail Models. NACA RM A51H20 (NACA/TIB/2944), 1951.Google Scholar
8.The Effect of Boundary Layer Thickness on the Ram- Recovery of Flush Intakes. A. V. Roe and Co Ltd, Wind Tunnel Report No 698/65, 1952.Google Scholar
9.The Effect of Boundary Layer Thickness on the Ram- Recovery Ratio of an NACA Flush Intake. A. V. Roe and Co Ltd, Wind Tunnel Report No 698/80, 1953.Google Scholar
10.Tests on the NACA-Type Flush Air Intake Fitted to the Sundstrand Alternator and Oil-Cooler Units. A. V. Roe and Co Ltd, Wind Tunnel Report ARD/WT/698/179, 1958.Google Scholar
11.Unpublished Data from the Aircraft Research Association, Bedford, 1966.Google Scholar
12.Subsonic Performance Data for NACA-Type Submerged Air Intakes. RAeS Aerodynamics Data Sheet 66029, 1966.Google Scholar