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Supersonic far-field boundary conditions for transonic small-disturbance theoryCharacteristic far-field boundary conditions for supersonic freestream flow have been developed and implemented within a transonic small-disturbance code. The boundary conditions have been implemented within the CAP-TSD code which has been developed recently for aeroelastic analysis of complete aircraft configurations. These boundary conditions improve the accuracy of the solutions for supersonic freestream applications. They also allow the extent of the grid to be much smaller, thus providing savings in the computational time required to obtain solutions. Comparisons are shown between surface pressures computed using large and small grid extents for the NACA 0012 airfoil and the F-5 wing at various Mach numbers and angles of attack. Both steady and unsteady results are presented and comparisons are made with Euler results and with experimental data to assess the accuracy of the new far-field boundary conditions. Comparisons of these results show that the supersonic boundary conditions allow a much smaller grid to be used without losing accuracy.
Document ID
19890043394
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gibbons, Michael D.
(PRC Systems Services Hampton, VA, United States)
Batina, John T.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 89-1283
Meeting Information
Meeting: AIAA, ASME, ASCE, AHS, and ASC, Structures, Structural Dynamics and Materials Conference
Location: Mobile, AL
Country: United States
Start Date: April 3, 1989
End Date: April 5, 1989
Accession Number
89A30765
Distribution Limits
Public
Copyright
Other

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