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TITLE AND SUBTITLE:
Benchmark Solutions for Computational Aeroacoustics (CAA) Code Validation
AUTHOR(S):
Scott, James, R.
REPORT DATE:
2004-12-xx
FUNDING NUMBERS:
WBS-22-781-30-09
PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration John H. Glenn Research Center at Lewis Field Cleveland, Ohio 44135-3191
PERFORMING ORGANIZATION REPORT NUMBER:
E-14894
SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration Washington, DC 20546-0001
REPORT TYPE AND DATES COVERED:
Technical Memorandum
SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA/TM-2004-213386; IMECE2004-59865
SUPPLEMENTARY NOTES:
Prepared for the 2004 International Mechanical Engineering Congress and RD&D Exposition sponsored by the American Society of Mechanical Engineers, Anaheim, California, November 13-19, 2004. Responsible person, James R. Scott, organization code, 5940, 216-433-5863.
ABSTRACT:
NASA has conducted a series of Computational Aeroacoustics (CAA) Workshops on Benchmark Problems to develop a set of realistic CAA problems that can be used for code validation. In the Third (1999) and Fourth (2003) Workshops, the single airfoil gust response problem, with real geometry effects, was included as one of the benchmark problems. Respondents were asked to calculate the airfoil RMS pressure and far-field acoustic intensity for different airfoil geometries and a wide range of gust frequencies. This paper presents the validated that have been obtained to the benchmark problem, and in addition, compares them with classical flat plate results. It is seen that airfoil geometry has a strong effect on the airfoil unsteady pressure, and a significant effect on the far-field acoustic intensity. Those parts of the benchmark problem that have not yet been adequately solved are identified and presented as a challenge to the CAA research community.
SUBJECT TERMS:
Unsteady aerodynamics; Euler equations of motion; Gusts; Noise prediction (aircraft); Aircraft noise; Aeroacoustics; Computational fluid dynamics
NUMBER OF PAGES:
19
PDF AVAILABLE FROM URL:
2004/TM-2004-213386.pdf ( 580 KB )
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