Laminar to turbulent boundary layer transition is sensitive to wall temperature distribution and freestream disturbances. The wall temperature can increase the boundary layer thickness and affect the growth rate of disturbances in the boundary layer. Additionally, the receptivity and growth mechanisms in the boundary layer can capture and grow small amplitude disturbances that eventually cause transition. The goal of this paper is to use new capabilities to better inform the PSE analysis and introduce the feasibility of performing receptivity analysis with DNS. The ascent trajectory for HIFiRE-1 is simulated using a loosely coupled conjugate heat transfer solver. The wall temperature data is then used as a boundary condition for the PSE analysis. The PSE analysis agreed with prior analysis for hypersonic blunt nose cones. Furthermore, the PSE results showed large differences in the second-mode growth rate depending on the treatment of the wall temperature boundary condition. Finally, the capability for performing receptivity analysis with DNS is verified for a simple test case. Future work will use this new capability for inputting freestream disturbances into the flow field for HIFiRE-1.
|Original language||English (US)|
|Title of host publication||AIAA AVIATION 2020 FORUM|
|Publisher||American Institute of Aeronautics and Astronautics Inc, AIAA|
|State||Published - 2020|
|Event||AIAA AVIATION 2020 FORUM - Virtual, Online|
Duration: Jun 15 2020 → Jun 19 2020
|Name||AIAA AVIATION 2020 FORUM|
|Conference||AIAA AVIATION 2020 FORUM|
|Period||6/15/20 → 6/19/20|
Bibliographical noteFunding Information:
This work was sponsored by the Air Force Office of Scientific Research (AFOSR) under grants FA9550-18-0009 and FA9550-17-0250. 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 AFOSR or the U.S. Government. The authors would like to thank GoHypersonic, Inc. for providing Link3D grid generation software.
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
Copyright 2020 Elsevier B.V., All rights reserved.