TY - GEN
T1 - Numerical investigation of the effects of wall heating and cooling on the nonlinear transition stages for a sharp cone at Mach 6
AU - Herman, Briannah
AU - Hader, Christoph
AU - Fasel, Hermann F.
N1 - Funding Information:
This work was supported by AFOSR Grant FA9550-19-1-0208, with Dr. Sarah Popkin serving as the program manager. Computer time was provided by the University of Arizona High Performance Computing (HPC) center and the Department of Defense (DoD) High Performance Computing Modernization Program (HPCMP). The views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of the Air Force Office of Scientific Research or the U. S. Government.
Publisher Copyright:
© 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2022
Y1 - 2022
N2 - Direct Numerical Simulations (DNS) were carried out to investigate the effect of wall heating and cooling on the primary and secondary instability regimes for a 7◦ half-angle straight (right) cone at Mach 6 and zero angle of attack. Typical flow conditions of the Boeing/AFOSR Mach 6 Quiet Tunnel (BAM6QT) at Purdue University was used for the numerical investigations. As expected, regarding the primary wall cooling resulted in a destabilization of the second mode and a stabilization of the first mode, while wall heating had the opposite effect. Wall cooling resulted in a slight reduction of the nonlinear primary wave saturation amplitudes. Wall heating changed the saturation behavior significantly. While for the reference (Tw = 300 K) and cooled wall cases the maximum second mode (saturation) amplitude remains nearly constant after saturation onset, the amplitude continued to increase in the heated case, although at a significantly reduced growth rate compared to the linear stage. In addition, grid convergence investigations showed that for a heated wall case a substantially finer grid resolution is required to accurately capture the primary wave (nonlinear) saturation process. The secondary instability investigations indicated that wall cooling results in larger secondary amplification rates.
AB - Direct Numerical Simulations (DNS) were carried out to investigate the effect of wall heating and cooling on the primary and secondary instability regimes for a 7◦ half-angle straight (right) cone at Mach 6 and zero angle of attack. Typical flow conditions of the Boeing/AFOSR Mach 6 Quiet Tunnel (BAM6QT) at Purdue University was used for the numerical investigations. As expected, regarding the primary wall cooling resulted in a destabilization of the second mode and a stabilization of the first mode, while wall heating had the opposite effect. Wall cooling resulted in a slight reduction of the nonlinear primary wave saturation amplitudes. Wall heating changed the saturation behavior significantly. While for the reference (Tw = 300 K) and cooled wall cases the maximum second mode (saturation) amplitude remains nearly constant after saturation onset, the amplitude continued to increase in the heated case, although at a significantly reduced growth rate compared to the linear stage. In addition, grid convergence investigations showed that for a heated wall case a substantially finer grid resolution is required to accurately capture the primary wave (nonlinear) saturation process. The secondary instability investigations indicated that wall cooling results in larger secondary amplification rates.
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U2 - 10.2514/6.2022-0601
DO - 10.2514/6.2022-0601
M3 - Conference contribution
AN - SCOPUS:85123289508
SN - 9781624106316
T3 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
BT - AIAA SciTech Forum 2022
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
Y2 - 3 January 2022 through 7 January 2022
ER -