- Restrictions on Access:
- Unclassified, Unlimited, Publicly available.
- A predictive tool for estimating the onset of boundary layer transition resulting from damage to and/or repair of the thermal protection system was developed in support of Shuttle Return to Flight. The boundary layer transition tool is part of a suite of tools that analyze the aerothermodynamic environment to the local thermal protection system to allow informed disposition of damage for making recommendations to fly as is or to repair. Using mission specific trajectory information and details of each damage site or repair, the expected time (and thus Mach number) at transition onset is predicted to help define the aerothermodynamic environment to use in the subsequent thermal and stress analysis of the local thermal protection system and structure. The boundary layer transition criteria utilized for the tool was developed from ground-based measurements to account for the effect of both protuberances and cavities and has been calibrated against select flight data. Computed local boundary layer edge conditions were used to correlate the results, specifically the momentum thickness Reynolds number over the edge Mach number and the boundary layer thickness. For the initial Return to Flight mission, STS-114, empirical curve coefficients of 27, 100, and 900 were selected to predict transition onset for protuberances based on height, and cavities based on depth and length, respectively.
- NASA Technical Reports Server (NTRS) Collection.
- Document ID: 20060022550.
AIAA Paper 2006-2918.
9th AIAA/ASME Joint Thermophysics and Heat Transfer Conference; 5-8 Jun. 2006; San Francisco, CA; United States.
- Copyright, Distribution as joint owner in the copyright.
View MARC record | catkey: 16003510