TY - GEN
T1 - Direct numerical simulations of laminar-turbulent transition for transonic boundary layers
AU - Hader, Christoph
AU - Deng, Ning
AU - Woodward, Michael
AU - Fasel, Hermann F.
N1 - Funding Information:
This work was supported by W911NF-20-S-0006, with Dr. Matthew Munson serving as the program manager. Computer time was provided by the US Army Engineering Research and Development Center (ERDC) under 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:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2021
Y1 - 2021
N2 - Direct Numerical Simulations (DNS) were carried out to investigate laminar-turbulent boundary-layer transition on a 5◦ opening half-angle straight (right) cone with a sharp nose tip at zero angle of attack for the transonic flow regime (M = 0.8 − 1.2). The cone geometry and flow conditions of the in-flight transition experiments by the National Aeronautics and Space Administration (NASA) were used for the numerical investigations. Linear Stability Theory (LST) analysis has shown that strongly amplified axisymmetric and oblique disturbance waves exist for the flow conditions investigated here. A highly-resolved three-dimensional DNS for M = 1.08 of a wave packet, initiated by a short duration pulse via a blowing and suction hole at the wall, demonstrated that a fully developed turbulent spot develops rapidly (over a short downstream distance) from a short-duration pulse disturbance. Results from the DNS of the nonlinear wavepacket and turbulent development are presented and discussed in this paper.
AB - Direct Numerical Simulations (DNS) were carried out to investigate laminar-turbulent boundary-layer transition on a 5◦ opening half-angle straight (right) cone with a sharp nose tip at zero angle of attack for the transonic flow regime (M = 0.8 − 1.2). The cone geometry and flow conditions of the in-flight transition experiments by the National Aeronautics and Space Administration (NASA) were used for the numerical investigations. Linear Stability Theory (LST) analysis has shown that strongly amplified axisymmetric and oblique disturbance waves exist for the flow conditions investigated here. A highly-resolved three-dimensional DNS for M = 1.08 of a wave packet, initiated by a short duration pulse via a blowing and suction hole at the wall, demonstrated that a fully developed turbulent spot develops rapidly (over a short downstream distance) from a short-duration pulse disturbance. Results from the DNS of the nonlinear wavepacket and turbulent development are presented and discussed in this paper.
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M3 - Conference contribution
AN - SCOPUS:85100105212
SN - 9781624106095
T3 - AIAA Scitech 2021 Forum
SP - 1
EP - 12
BT - AIAA Scitech 2021 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021
Y2 - 11 January 2021 through 15 January 2021
ER -