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Calculation of the Lateral Coefficient Corrections for an Aircraft Model with Rear Sting Support in Subsonic Wind Tunnel Flow

Steinbach, D. (1997) Calculation of the Lateral Coefficient Corrections for an Aircraft Model with Rear Sting Support in Subsonic Wind Tunnel Flow. Aerospace Science and Technology, Vol. 15 (No. 1), pp. 27-36.

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Abstract

For a fighter type aircraft like the TST Alpha-Jet model the aerodynamic coefficient corrections for unsymmetric windtunnel flows are calculted. The model is attached to a rear sting support system and placed in the test-section of a subsonic windtunnel (KKK at DLR Koeln) at incidence and yaw. For the numerical simulation of the windtunnel flow a subsonic panel method is used. The results are given in the form of windtunnel and support corrections for the lateral model coefficients side force, yawing and rolling moment.

Document Type:Article
Additional Information: LIDO-Berichtsjahr=1997,
Title:Calculation of the Lateral Coefficient Corrections for an Aircraft Model with Rear Sting Support in Subsonic Wind Tunnel Flow
Authors:
AuthorsInstitution or Email of Authors
Steinbach, D.UNSPECIFIED
Date:1997
Journal or Publication Title:Aerospace Science and Technology
Refereed publication:Yes
In ISI Web of Science:Yes
Volume:Vol. 15
Page Range:pp. 27-36
Status:Published
Keywords:lateral coefficient corrections, TST Alpha-Jet model in KKK, subsonic panel method
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:other
DLR - Research area:Aeronautics
DLR - Program:L SI - Versuchs- und Simulationstechniken
DLR - Research theme (Project):UNSPECIFIED
Location: Köln-Porz , Braunschweig , Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Institut für Strömungsmechanik > Institut für Theoretische Strömungsmechanik
Deposited By: elib DLR-Beauftragter
Deposited On:03 Apr 2006
Last Modified:27 Apr 2009 10:36

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