A CFD/CSD interaction methodology for aircraft wings

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With advanced subsonic transports and military aircraft operating in the transonic regime, it is becoming important to determine the effects of the coupling between aerodynamic loads and elastic forces. Since aeroelastic effects can significantly impact the design of these aircraft, there is a strong need in the aerospace industry to predict these interactions computationally. Such an analysis in the transonic regime requires high fidelity computational fluid dynamics (CFD) analysis tools, due to the nonlinear behavior of the aerodynamics in the transonic regime and also high fidelity computational structural dynamics (CSD) analysis tools. Also, there is a need to be able ... continued below

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37 p.

Creation Information

Bhardwaj, M.K.; Kapania, R.K.; Reichenbach, E. & Guruswamy, G.P. January 1, 1998.

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  • Sandia National Laboratories
    Publisher Info: Sandia National Labs., Albuquerque, NM (United States)
    Place of Publication: Albuquerque, New Mexico

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Description

With advanced subsonic transports and military aircraft operating in the transonic regime, it is becoming important to determine the effects of the coupling between aerodynamic loads and elastic forces. Since aeroelastic effects can significantly impact the design of these aircraft, there is a strong need in the aerospace industry to predict these interactions computationally. Such an analysis in the transonic regime requires high fidelity computational fluid dynamics (CFD) analysis tools, due to the nonlinear behavior of the aerodynamics in the transonic regime and also high fidelity computational structural dynamics (CSD) analysis tools. Also, there is a need to be able to use a wide variety of CFD and CSD methods to predict aeroelastic effects. Since source codes are not always available, it is necessary to couple the CFD and CSD codes without alteration of the source codes. In this study, an aeroelastic coupling procedure is developed to determine the static aeroelastic response of aircraft wings using any CFD and CSD code with little code integration. The aeroelastic coupling procedure is demonstrated on an F/A-18 Stabilator using NASTD (an in-house McDonnell Douglas CFD code) and NASTRAN. In addition, the Aeroelastic Research Wing (ARW-2) is used for demonstration of the aeroelastic coupling procedure by using ENSAERO (NASA Ames Research Center CFD code) and a finite element wing-box code. The results obtained from the present study are compared with those available from an experimental study conducted at NASA Langley Research Center and a study conducted at NASA Ames Research Center using ENSAERO and modal superposition. The results compare well with experimental data.

Physical Description

37 p.

Notes

OSTI as DE98005767

Source

  • 7. symposium on multidisciplinary analysis and optimization, St. Louis, MO (United States), 2-4 Sep 1998

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  • Other: DE98005767
  • Report No.: SAND--98-0136C
  • Report No.: CONF-980909--
  • Grant Number: AC04-94AL85000
  • DOI: 10.2172/658442 | External Link
  • Office of Scientific & Technical Information Report Number: 658442
  • Archival Resource Key: ark:/67531/metadc702492

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  • January 1, 1998

Added to The UNT Digital Library

  • Sept. 12, 2015, 6:31 a.m.

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  • April 14, 2016, 3:20 p.m.

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Bhardwaj, M.K.; Kapania, R.K.; Reichenbach, E. & Guruswamy, G.P. A CFD/CSD interaction methodology for aircraft wings, report, January 1, 1998; Albuquerque, New Mexico. (digital.library.unt.edu/ark:/67531/metadc702492/: accessed August 23, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.