Analysis of Ablation on Boundary Layer Stability of the Reentry F Flight Vehicle

Evan Rogers, Olivia M Schroeder, Luke Melander, Graham V. Candler

Research output: Chapter in Book/Report/Conference proceedingConference contribution


Boundary layer stability at hypersonic speeds is sensitive to small flow field changes. Nose tip ablation has multi-physical effects on the flow field that can potentially stabilize or destabilize the boundary layer by modifying the geometry, introducing additional chemical species, and changing the wall temperature profile. The objective of this work is to investigate how non-spherical nose tip blunting affects boundary layer stability for the Reentry F flight vehicle. A portion of the Reentry F flight experiment trajectory is simulated using a coupled fluid-solid solver which includes conjugate heat transfer (CHT) and gas surface interaction (GSI) models. The resulting base flows with GSI modeled are used to compute a species mass flux of carbon from the nose tip, which is then used to determine an approximate recession rate as the flight vehicle descended from 100,000 ft (30.48 km) to 80,000 ft (24.38 km). A total recession distance is then computed and new grids are constructed for base flow computation and stability analysis. A sensitivity study of the effect of recession on boundary layer stability is then completed for 1x, 1.5x, and 2x the nominal recession using the parabolized stability equations (PSE). It is observed that this non-spherical blunting has strong destabilizing effects upstream of approximately 1 m, while the downstream boundary layer stability is unaffected.

Original languageEnglish (US)
Title of host publicationAIAA AVIATION 2022 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624106354
StatePublished - 2022
EventAIAA AVIATION 2022 Forum - Chicago, United States
Duration: Jun 27 2022Jul 1 2022

Publication series

NameAIAA AVIATION 2022 Forum


ConferenceAIAA AVIATION 2022 Forum
Country/TerritoryUnited States

Bibliographical note

Funding Information:
The primary author is funded by the Select Graduate Training Program of the U.S. Naval Research Laboratory (NRL). The second author is funded by a NASA Space Technology Graduate Research Opportunities (NSTGRO) under Grant Number 80NSSC18K1150. The third author is 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 NRL or the U.S. Government.

Publisher Copyright:
© 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.


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