TY - GEN
T1 - Compressible mixing layer experiments for cfd validation
AU - Dutton, J. Craig
AU - Elliott, Gregory S.
AU - Kim, Kevin U.
N1 - Funding Information:
The authors would like to thank NASA for its financial support of this project through the D.3 Transformational Tools and Technologies Project (TTT) issued by NASA Headquarters: Award No. NNX15AU94A. Dr. Mujeeb Malik is the project manager for this program. We would also like to acknowledge the continuing technical support and assistance of our project technical managers at NASA Glenn Research Center: Jim DeBonis, Dave Davis, Nick Georgiadis, Dennis Yoder, and Manan Vyas. Finally, we would like to thank UIUC lecturer Blake Johnson, graduate student Gyu Sub Lee, and undergraduate students Will Yoshida, Brandon Ngai, and Tim Wagner for their assistance with various aspects of the facility design, experiments, and website documentation.
Publisher Copyright:
© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2019
Y1 - 2019
N2 - A comprehensive experimental study is described whose fundamental objective is to obtain CFD validation-quality measurements of turbulent, compressible mixing layers on a highly spatially resolved basis. A wide range of convective Mach numbers has been considered, varying from roughly Mc = 0.2 – 0.9, or essentially incompressible to highly compressible conditions. Schlieren and Mie scattering flow visualizations and axial static pressure measurements are used to establish neutral pressure gradient conditions along the mixing layer in each case. The boundary and initial conditions for each shear layer are documented, particularly the incoming boundary layers and freestreams on the four tunnel centerplane walls approaching the splitter-plate tip. Stereo PIV (SPIV) measurements in each mixing layer are of primary importance, including all three components of the mean velocity, the full Reynolds stress tensor, and higher-order moments. Care has been taken to clearly establish that fully-developed, self-similar conditions are reached for each mixing layer in the far field. In addition, the uncertainties for the critical SPIV measurements have been considered in detail. The website address is given at which all results of the current study are available for each case, including the test-section geometry, boundary and initial conditions, all flow visualizations, pressure and velocity measurements, as well as associated experimental uncertainties.
AB - A comprehensive experimental study is described whose fundamental objective is to obtain CFD validation-quality measurements of turbulent, compressible mixing layers on a highly spatially resolved basis. A wide range of convective Mach numbers has been considered, varying from roughly Mc = 0.2 – 0.9, or essentially incompressible to highly compressible conditions. Schlieren and Mie scattering flow visualizations and axial static pressure measurements are used to establish neutral pressure gradient conditions along the mixing layer in each case. The boundary and initial conditions for each shear layer are documented, particularly the incoming boundary layers and freestreams on the four tunnel centerplane walls approaching the splitter-plate tip. Stereo PIV (SPIV) measurements in each mixing layer are of primary importance, including all three components of the mean velocity, the full Reynolds stress tensor, and higher-order moments. Care has been taken to clearly establish that fully-developed, self-similar conditions are reached for each mixing layer in the far field. In addition, the uncertainties for the critical SPIV measurements have been considered in detail. The website address is given at which all results of the current study are available for each case, including the test-section geometry, boundary and initial conditions, all flow visualizations, pressure and velocity measurements, as well as associated experimental uncertainties.
UR - http://www.scopus.com/inward/record.url?scp=85098248777&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85098248777&partnerID=8YFLogxK
U2 - 10.2514/6.2019-2847
DO - 10.2514/6.2019-2847
M3 - Conference contribution
AN - SCOPUS:85098248777
SN - 9781624105890
T3 - AIAA Aviation 2019 Forum
BT - AIAA Aviation 2019 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Aviation 2019 Forum
Y2 - 17 June 2019 through 21 June 2019
ER -