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A prediction method for the influence of a turbulent boundary layer on the efficiency of submerged intakes

Published online by Cambridge University Press:  04 July 2016

A. J. Ward-Smith
A. J. Ward-Smith*
Affiliation:
Brunel University
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Extract

The deterioration in the performance of NACA submerged intakes in the presence of a boundary layer has been established in Ref. 12, where a correlation of experimental data, obtained from wind tunnel tests on models, is presented. The purpose of this paper is to provide a prediction method which will allow the efficiency of these intakes to be estimated outside the range for which experimental data exist.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 77 , Issue 755 , November 1973 , pp. 570 - 574
Copyright
Copyright © Royal Aeronautical Society 1973 

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References

1. Mossman, E. A. and Randall, L. M. An experimental investigation of the design variables for NACA submerged duct entrances. NACA RM No A7130 (NACA/ TIB/1563). 1948.Google Scholar
2 Delany, N. K.. An investigation of submerged air intakes on a 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 A8129 (NACA/TIB/1970). 1948.Google Scholar
5. Axelson, J. A. and Taylor, R. A. Preliminary investigation of the transonic characteristics of an NACA sub merged 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 sub sonic 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-fall 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. McCreath, K. M. and Ward Smith, A. J. Boundary layer influence on the performance of submerged intakes. The Aeronautical Journal of the Royal Aeronautical Society, August 1967, p. 581.Google Scholar