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Chapter 1 – Static and Dynamic SACCON PIV Tests - Part II: Aft Flow Field

Konrath, Robert and Roosenboom, Eric and Schröder, Andreas and Pallek, Dieter and Otter, Dirk (2012) Chapter 1 – Static and Dynamic SACCON PIV Tests - Part II: Aft Flow Field. Project Report. AVT-161, 848 S.

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Official URL: http://www.cso.nato.int/Pubs/rdp.asp?RDP=RTO-TR-AVT-161


The flow above delta wing shaped UCAV (Unmanned Combat Air Vehicle) configurations is often dominated by strong vortices, especially at moderate and high angle of attack. On delta wings with sharp leading edges, the flow separates at the leading edges already at small angles of attack. The shear layer rolls up and two vortices are formed on each side of the wing starting close to the wing apex and increasing in size towards the wing aft. The vortices produce strong suction peaks on the upper wing surface, so that additional lift is generated which is of benefit by performing low speed manoeuvres like take-off and landing. UCAV configurations often consist of rounded leading edges to improve their performance under cruise conditions. In this case the flow topology becomes more complicated because the flow separations at the leading edges are delayed to higher angles of attack and depend strongly on the Reynolds and Mach number. In regions of attached flow around blunt leading edges, other flow effects may produce additional vortices as observed on the VFE2 delta wing where vortices develop inboard the leading edge vortices caused by a kind of instability within the boundary layer. The onset of the leading edge vortices, their interactions and accompanying phenomena like vortex breakdown can cause adverse loading effects. To avoid such non-linear aerodynamic characteristics detailed flow investigations are of great importance during the design chain by improving the understanding of the aerodynamics. This all the more so if the dynamic behaviour of the vehicle has to be considered as the flow effects become even further complicated. Within the scope of the Task Group of AVT-161 (Chapter 1), Stereoscopic Particle Image Velocimetry (PIV) has been applied for flow field investigations on a SACCON (Stability And Control CONfiguration) wind tunnel model.

Item URL in elib:https://elib.dlr.de/70654/
Document Type:Monograph (Project Report)
Additional Information:This document is distributed in accordance with NATO Security Regulations and RTO policies and is RELEASABLE TO AUSTRALIA AND SWEDEN
Title:Chapter 1 – Static and Dynamic SACCON PIV Tests - Part II: Aft Flow Field
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Date:September 2012
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Number of Pages:848
EditorsEmailEditor's ORCID iD
UNSPECIFIEDNATO Science and Technology OrganizationUNSPECIFIED
Series Name:Summary Report of the NATO RTO AVT-161 TASK Group
Keywords:UCAV (Unmanned Combat Air Vehicle), boundary layer, Stereoscopic Particle Image Velocimetry (PIV)
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 - Simulation & Validation (old)
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Experimental Methods
Deposited By: Micknaus, Ilka
Deposited On:26 Nov 2012 14:57
Last Modified:26 Nov 2012 14:57

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