Abstract
An experimental study of the effect of vortex ingestion into an S-duct diffuser on flow conditions at the engine face is presented. A simultaneous ingestion of a boundary layer is also considered. In order to form a boundary layer of well-defined thickness ahead of the intake the diffuser is arranged on a flat plate. The dependence of the circulation of the ingested vortex on the flow in the diffuser has been examined in a parametric study in a blow-down wind tunnel. The free-stream Mach number was varied between M = 0.30 and M = 0.65 at a fixed mass flow. In the introduction the importance of boundary layer ingesting highly integrated intakes is briefly discussed. This is followed by a description of the analytical design of the generic intake model, the cryogenic blowdown tunnel DNW-KRG in which the experimental tests have been performed, and the measurement techniques. Thereafter, experimental findings are discussed in detail and conclusions are drawn.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
References
Arntz, A., Atinault, O., Destarac, D., Merlen, A.: Exergy-based aircraft aeropropulsive performance assessment: CFD application to boundary layer ingestion. AIAA 2014-2573 (2014)
Rein, M., Koch, S.: Experimental study of boundary-layer ingestion into a diverterless S-duct intake. J. Aircr. Tech. Note 53(11) (2015)
Koch, S., Rütten, M., Rein, M.: Experimental and numerical investigations on integrated intakes for agile and highly swept aircraft configurations. DGLR Paper-0173, Deutscher Luft- und Raumfahrtkongress, Rostock (2015). (urn:nbn:de:101:1-201510306355)
Berens, T., Delot, A.-L., Tormalm, M., Ruiz-Calavera, L.-P., Funes-Sebastian, D.-E., Rein, M., Säterskog, M., Ceresola, N., Zurawski, L., Numerical and experimental investigations on highly integrated subsonic air intakes. AIAA 2014-0722 (2014)
Rein, M., Hannemann, M., Gardner, A.D., Koch, S.: Design of a Generic Subsonic S-Duct Intake for Studies on the Effect of Boundary Layer Ingestion. DLR, Germany Aerospace Center, IB-224-2009-A28, Göttingen, Germany (2009)
Rosemann, H.: The cryogenic ludwieg-tube tunnel at Göttingen. Special Course on Advances in Cryogenic Wind Tunnel Technology, AGARD Reports 812, pp. 8.1–8.13 (1997)
Seddon, J.J., Goldsmith, E.L.: Intake Aerodynamics, 2nd edn, p. 271. AIAA, Reston, VA (1999)
Gerhold, T., Evans, J.: Efficient Computation of 3D-Flows for Complex Configurations with the DLR Tau-Code Using Automatic Adaptation. Notes on Numerical Fluid Mechanics, vol. 72. Vieweg (1999)
Schwamborn, D., Gardner, A., von Geyr, H., Krumbein, A., Lüdeke, H., Stürmer, A.: Development of the TAUCode for aerospace applications. In: 50th NAL International Conference on Aerospace Science and Technology, 26–28 June 2008, Bangalore, India (2008)
Author information
Authors and Affiliations
Corresponding author
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 2018 Springer International Publishing AG
About this paper
Cite this paper
Koch, S., Rütten, M., Rein, M. (2018). Study of Total Pressure Losses at the Engine Face of a Submerged Inlet with an Ingested Vortex. In: Dillmann, A., et al. New Results in Numerical and Experimental Fluid Mechanics XI. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 136. Springer, Cham. https://doi.org/10.1007/978-3-319-64519-3_33
Download citation
DOI: https://doi.org/10.1007/978-3-319-64519-3_33
Published:
Publisher Name: Springer, Cham
Print ISBN: 978-3-319-64518-6
Online ISBN: 978-3-319-64519-3
eBook Packages: EngineeringEngineering (R0)