Steady and unsteady aeroelastic computations of HIRENASD wing for low and high Reynolds numbers

Pinar Acar, Melike Nikbay

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

8 Citations (Scopus)

Abstract

We perform static and dynamic aeroelastic analyses of the HIRENASD wing based on NASA's reference data delivered for two test cases with different flight conditions. The tests have been conducted in cryogenic medium to investigate steady and unsteady aeroelastic responses in transonic regime for low and high Reynolds numbers. For computational studies, the latest structural model of NASA is used. First, a free vibration analysis is performed in Nastran. Then, the modal solution is imported from the finite element solver to ZEUS, where the aerodynamic model and fluid structure interaction parameters are constructed. Steady and unsteady aeroelastic results are examined for the specified stations along the wing span, and interpolated for chordwise direction so as to match them with the wind tunnel test points. The designated output parameters such as steady aerodynamic lift, moment and drag coefficients, and steady and unsteady pressure distributions along the chordwise direction are compared to the experimental results.

Original languageEnglish
Title of host publication54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
DOIs
Publication statusPublished - 2013
Event54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference - Boston, MA, United States
Duration: 8 Apr 201311 Apr 2013

Publication series

Name54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

Conference

Conference54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Country/TerritoryUnited States
CityBoston, MA
Period8/04/1311/04/13

Funding

The HIRENASD (HIgh REynolds Number Aero-Structural Dynamics) project was initiated at RWTH Aachen University in 2004. The main purpose of this project is to analyze steady and unsteady aeroelastic experiments in transonic flight regime with a supercritical elastic wing model.5 The HIRENASD wind-tunnel model was tested in the European Transonic Windtunnel (ETW) in 2006 by Aachen University’s Department of Mechanics with funding from the German Research Foundation.6 The test medium of ETW is nitrogen gas under cryogenic conditions.5 The HIRENASD wing model corresponds to the SFB 401 clean wing reference configuration with a planview typical for wings of high speed transport aircrafts.7 The wing has a 34o degree of backward sweep angle and a supercritical wing profile BAC 3-11. The aerodynamic reference

FundersFunder number
European Transonic Windtunnel

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