TY - GEN
T1 - Shock-Buffet Prediction Report in Support of the High-Angle Working Group at the Third Aeroelastic Prediction Workshop
AU - Chwalowski, Pawel
AU - McHugh, Garrett R.
AU - Massey, Steven J.
AU - Poplingher, Lior
AU - Raveh, Daniella E.
AU - Jirasek, Adam
AU - Seidel, Jurgen
AU - Giannelis, Nicholas F.
AU - Vio, Gareth A.
AU - Venkatraman, Kartik
AU - Singh, Magan
AU - Ahrabi, Behzad R.
AU - Hong, Moeljo
AU - Slotnick, Jeffrey
N1 - Publisher Copyright: © 2024 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2024
Y1 - 2024
N2 - This paper presents a summary of the computational shock-buffet results associated with the third Aeroelastic Prediction Workshop (AePW-3) High-Angle Working Group. The computational results are compared against experimental data collected during the Oscillating Turn Table (OTT) Benchmark Supercritical Wing (BSCW) test campaign conducted in NASA Langley Research Center Transonic Dynamics Tunnel (TDT) in early 2000. In addition to experimental forced oscillation data, unsteady pressure data was collected at a single spanwise station at transonic Mach numbers, several values of dynamic pressure, and fixed angles of attack. It is acknowledged that the current experimental data sets are limited, but future experiments are planned to obtain pressure data at two wingspan stations in addition to unsteady Pressure Sensitive Paint (uPSP). With that, the computational results presented here are considered to be semi-blind. The results are presented in the form of time-varying pressure coefficients, running-mean values of the pressure coefficients, Power Spectral Density (PSD) and Strouhal number computations. The results are split into two parts. In the first part, the computational results obtained by each team using their flow solvers and grids are compared. In the second part, a single computational tool was used to compute unsteady pressure on participant-generated grids. In addition, a description of each participating team’s software and methods is included.
AB - This paper presents a summary of the computational shock-buffet results associated with the third Aeroelastic Prediction Workshop (AePW-3) High-Angle Working Group. The computational results are compared against experimental data collected during the Oscillating Turn Table (OTT) Benchmark Supercritical Wing (BSCW) test campaign conducted in NASA Langley Research Center Transonic Dynamics Tunnel (TDT) in early 2000. In addition to experimental forced oscillation data, unsteady pressure data was collected at a single spanwise station at transonic Mach numbers, several values of dynamic pressure, and fixed angles of attack. It is acknowledged that the current experimental data sets are limited, but future experiments are planned to obtain pressure data at two wingspan stations in addition to unsteady Pressure Sensitive Paint (uPSP). With that, the computational results presented here are considered to be semi-blind. The results are presented in the form of time-varying pressure coefficients, running-mean values of the pressure coefficients, Power Spectral Density (PSD) and Strouhal number computations. The results are split into two parts. In the first part, the computational results obtained by each team using their flow solvers and grids are compared. In the second part, a single computational tool was used to compute unsteady pressure on participant-generated grids. In addition, a description of each participating team’s software and methods is included.
UR - http://www.scopus.com/inward/record.url?scp=85197802804&partnerID=8YFLogxK
U2 - https://doi.org/10.2514/6.2024-0417
DO - https://doi.org/10.2514/6.2024-0417
M3 - منشور من مؤتمر
SN - 9781624107115
T3 - AIAA SciTech Forum and Exposition, 2024
BT - AIAA SciTech Forum and Exposition, 2024
T2 - AIAA SciTech Forum and Exposition, 2024
Y2 - 8 January 2024 through 12 January 2024
ER -