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

Analysis of the transonic flow around a generic UCAV configuration

Zimper, Dirk and Hummel, Dietrich (2014) Analysis of the transonic flow around a generic UCAV configuration. In: 32nd AIAA Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics. AIAA AVIATION 2014, 16.-20. Jun. 2014, Atlanta, Georgia, USA. ISBN 978-1-62410-288-2 ISSN 2014-2266

[img] PDF - Registered users only

Official URL: http://arc.aiaa.org/doi/abs/10.2514/6.2014-2266


The present investigation has been carried out as part of the NATO/STO AVT-201 Task Group on “Extended Assessment of Reliable Stability & Control Prediction Methods for NATO Air Vehicles”. The SACCON configuration is considered. Its geometry as well as the low speed aerodynamics and the corresponding flow physics are well known from the literature: For medium angles of attack the flow around the leading edge is governed by three sections, namely an apex vortex in the front part, a region of attached flow in the middle portion and a tip vortex in the outer part of the leading edge. The size of these regions varies with the angle of attack. In the present study the compressible flow around this configuration has been calculated using the CFD TAU code in the Mach number range 0.55 ≤ M∞ ≤ 0.85 and angles of attack 0° ≤ α ≤ 16° for a constant Reynolds number Re = 23x106 corresponding to the cruise condition of the UCAV. With increasing Mach number the flow in the central region of the leading edge becomes supersonic. Therefore, the upstream movement of the tip vortex with increasing angle of attack is hindered. However, at the rear end of the supersonic zone shockinduced separation takes place forming an additional vortex. This shock-induced vortex joins the tip vortex. Thus, the onset of the tip vortex now moves again upstream with increasing angle of attack passing the rear end of the supersonic zone. The corresponding very complex vortex formation is analyzed by means of Mach number and angle of attack variation. The effects of these flow phenomena on the aerodynamic characteristics are demonstrated.

Item URL in elib:https://elib.dlr.de/89671/
Document Type:Conference or Workshop Item (Speech)
Title:Analysis of the transonic flow around a generic UCAV configuration
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Zimper, Dirkdirk.zimper (at) dlr.deUNSPECIFIED
Hummel, Dietrichdietrich.Hummel (at) tu-braunschweig.deUNSPECIFIED
Date:July 2014
Journal or Publication Title:32nd AIAA Applied Aerodynamics Conference
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Publisher:American Institute of Aeronautics and Astronautics
Keywords:UAV, UCAV, transonic flow, aerodynamic behaviour, SACCON, Stability & Control, Vortex, Shock Wave
Event Title:AIAA AVIATION 2014
Event Location:Atlanta, Georgia, USA
Event Type:international Conference
Event Dates:16.-20. Jun. 2014
Organizer:American Institute of Aeronautics and Astronautics
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Military Technologies, L - Flight Physics
Location: Köln-Porz
Institutes and Institutions:Program Coordination Defence & Security Research
Deposited By: Zimper, Dr.-Ing. Dirk
Deposited On:03 Sep 2014 14:26
Last Modified:06 Jun 2016 14:07

Repository Staff Only: item control page

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