elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

Numerical and Experimental Investigations on Highly Integrated Subsonic Air

Berens, Thomas M. and Delot, Anne-Laure and Tormalm, Magnus H. and Ruiz-Calavera, Luis P. and Funes-Sebastian, David E. and Rein, Martin and Säterskog, Michael and Ceresola, Nicola and Zurawski, Ludovic (2014) Numerical and Experimental Investigations on Highly Integrated Subsonic Air. 52nd Aerospace Sciences Meeting - AIAA SciTech, 13. - 17. Jan. 2014, National Harbor, Maryland, USA.

Full text not available from this repository.

Official URL: http://arc.aiaa.org | DOI: 10.2514/6.2014-0722

Abstract

Aerodynamic integration of air intakes and the optimization of their performance are challenging tasks for innovative design of advanced unmanned aerial vehicles (UAVs). The extension of Computational Fluid Dynamics (CFD) into application areas such as dynamic intake distortion prediction and thus engine/intake compatibility is made possible by modern hybrid methods and increasing computer resources. Within the Aerodynamics Action Group AD/AG-46 “Highly Integrated Subsonic Air Intakes” of the Group for Aeronautical Research and Technology in EURope (GARTEUR), CFD computations were carried out for the EIKON UAV configuration, which was designed and wind tunnel tested at FOI in Sweden. The major objectives of AD/AG-46 were to investigate the capability of Detached Eddy Simulation (DES) methods for the analysis of unsteady flow phenomena of serpentine air intakes and the accuracy levels of the computations. Numerical results for a variety of wind tunnel conditions were compared with Reynolds-Averaged Navier-Stokes (RANS) and unsteady RANS (URANS) data as well as with experimental results. The impact of not considering the wind tunnel walls in the CFD calculations on the computational results was investigated, revealing that the ventilated walls of the T1500 wind tunnel eliminate the blockage of the model within the closed test section and that free stream conditions can be applied for the computational boundary conditions. Since intake lip shaping is a vital design parameter impacting the intake internal flow and performance, the original geometry was compared with a modified cowl while maintaining low-observability features of the W-shaped cowl design. A trade-off study between boundary layer diversion versus ingestion was performed numerically by applying Euler boundary conditions to the walls of the numerical model of the UAV configuration, thus simulating the total removal or diversion of the boundary layer. The computed inviscid results were compared with the viscous data, quantifying the losses in total pressure recovery and the increase in distortion for the ingested test cases. Internal flow control in the intake duct of the UAV configuration was studied by numerically applying vortex generators, and the results were compared with experimental data. Numerical models were employed in order to simulate micro-jets as active flow control devices in the serpentine duct. Increasing of jet velocities resulted in smaller areas of flow separation and thus led to beneficial total pressure recoveries and distortion parameters. At DLR in Göttingen experiments with a generic high aspect ratio diverterless intake model were performed in the cryogenic blowdown wind tunnel DNW-KRG with the goal of contributing to a better understanding and correlation of installed performance predictions of highly integrated innovative intake designs. In a parametric study the combined effects of boundary layer ingestion and an S-shaped intake diffuser on total pressure recovery and distortion at the engine face were investigated as a function of Mach number, Reynolds number, boundary layer thickness, and intake mass flow ratio.

Item URL in elib:https://elib.dlr.de/88154/
Document Type:Conference or Workshop Item (Speech)
Additional Information:AIAA 2014-0722; Chapter DOI: 10.2514/6.2014-0722; eISBN: 978-1-62410-256-1; DOI: 10.2514/masm14
Title:Numerical and Experimental Investigations on Highly Integrated Subsonic Air
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Berens, Thomas M.CASSIDIAN EADS Deutschland GmbH, 85077 Manching, GermanyUNSPECIFIED
Delot, Anne-LaureONERA – The French Aerospace Lab, F-92190 Meudon, FranceUNSPECIFIED
Tormalm, Magnus H.Swedish Defence Research Agency (FOI), SE-16490 Stockholm, SwedenUNSPECIFIED
Ruiz-Calavera, Luis P.AIRBUS MILITARY, 28906 Getafe (Madrid), SpainUNSPECIFIED
Funes-Sebastian, David E.AIRBUS MILITARY, 28906 Getafe (Madrid), SpainUNSPECIFIED
Rein, Martinmartin.rein (at) dlr.deUNSPECIFIED
Säterskog, MichaelSAAB AB, Aeronautics, 58188 Linköping, SwedenUNSPECIFIED
Ceresola, NicolaALENIA AERMACCHI, 10146 Torino, ItalyUNSPECIFIED
Zurawski, LudovicMBDA, 92358 Le Plessis-Robinson, FranceUNSPECIFIED
Date:2014
Refereed publication:Yes
Open Access:No
In DOAJ:No
In SCOPUS:No
In ISI Web of Science:No
Page Range:pp. 1-42
Series Name:Conference Proceedings online
Status:Published
Keywords:S-duct intake, serpentine intake, diverterless intake, intake lip shaping, boundary layer ingestion, boundary layer diversion, circumferential distortion descriptor, DC60, AIP, DNW-KRG, pressure variations, detached eddy simulation (DES), Reynolds-averaged Navier-Stokes (RANS), unsteady RANS (URANS), flow control
Event Title:52nd Aerospace Sciences Meeting - AIAA SciTech
Event Location:National Harbor, Maryland, USA
Event Type:international Conference
Event Dates:13. - 17. Jan. 2014
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:Aircraft Research (old)
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Military Technologies (old)
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > High Speed Configurations
Deposited By: Micknaus, Ilka
Deposited On:17 Feb 2014 13:11
Last Modified:20 Oct 2014 13:55

Repository Staff Only: item control page

Browse
Search
Help & Contact
Information
electronic library is running on EPrints 3.3.12
Copyright © 2008-2017 German Aerospace Center (DLR). All rights reserved.