Abstract
Laminar to turbulent boundary layer transition is known to be sensitive to freestream disturbances. However, the disturbances in the upper atmosphere are not well characterized, and a multi-university effort to characterize turbulence and particle distributions in the stratosphere aims to address that. This paper considers the numerical methods associated with simulating shock-turbulence interactions for a hypersonic sphere-cone. Atmospheric turbulence is first generally characterized, and then a turbulent shear simulation is characterized in relation to hypersonic flight in order to establish a method for simulating the interaction between hypersonic vehicles and atmospheric turbulence. Low-dissipation Direct Numerical Simulation (DNS) methods for the compressible Navier-Stokes equations are compared with linear equations for planar wave and oblique shock interaction and found to accurately simulate the shock-disturbance interaction. Linear growth of boundary layer waves due to interaction with the second mode instability in hypersonic boundary layer is also simulated with low dissipation DNS and found to compare well with predictions from the Parabolized Stability Equations (PSE). Lastly, atmospheric turbulence in relation to hypersonic flight is discussed and simulation requirements to determine it’s effect on hypersonic boundary layer transition are discussed.
| Original language | English (US) |
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| Title of host publication | AIAA Scitech 2021 Forum |
| Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
| Pages | 1-14 |
| Number of pages | 14 |
| ISBN (Print) | 9781624106095 |
| State | Published - 2021 |
| Event | AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021 - Virtual, Online Duration: Jan 11 2021 → Jan 15 2021 |
Publication series
| Name | AIAA Scitech 2021 Forum |
|---|
Conference
| Conference | AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021 |
|---|---|
| City | Virtual, Online |
| Period | 1/11/21 → 1/15/21 |
Bibliographical note
Funding Information:This work was sponsored by the Air Force Office of Scientific Research (AFOSR) under grants FA9550-18-1-0009. 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.
Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.