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Experience with transonic unsteady aerodynamic calculationsComparisons of calculated and experimental transonic unsteady pressures and airloads for four of the AGARD Two Dimensional Aeroelastic Configurations and for a rectangular supercritical wing are presented. The two dimensional computer code, XTRAN2L, implementing the transonic small perturbation equation was used to obtain results for: (1) pitching oscillations of the NACA 64A010A; NLR 7301 and NACA 0012 airfoils; (2) flap oscillations for the NACA 64A006 and NRL 7301 airfoils; and (3) transient ramping motions for the NACA 0012 airfoils. Results from the three dimensional code XTRAN3S are compared with data from a rectangular supercritical wing oscillating in pitch. These cases illustrate the conditions under which the transonic inviscid small perturbation equation provides reasonable predictions.
Document ID
19840024283
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Edwards, J. W. (NASA Langley Research Center Hampton, VA, United States)
Bland, S. R. (NASA Langley Research Center Hampton, VA, United States)
Seidel, D. A. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
August 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:86278
NASA-TM-86278
Report Number: NAS 1.15:86278
Report Number: NASA-TM-86278
Meeting Information
Meeting: Meeting of the AGARD Struct. and Mater. Panel of the Spec. Meeting on Transonic Unsteady Aerodyn. and its Aeroelastic Appl.,
Location: Toulouse
Country: France
Start Date: September 2, 1984
End Date: September 7, 1984
Accession Number
84N32353
Funding Number(s)
PROJECT: RTOP 505-33-43
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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