Accession Number:

ADA622133

Title:

A Nonequilibrium Finite-Rate Carbon Ablation Model for Radiating Earth Re-entry Flows

Descriptive Note:

Doctoral thesis

Corporate Author:

AIR FORCE INSTITUTE OF TECHNOLOGY WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT

Personal Author(s):

Report Date:

2015-09-17

Pagination or Media Count:

204.0

Abstract:

Vehicles entering planetary atmospheres at high speed require an ablative heat shield in order to withstand the high thermal energy flux to the body. Numerical simulations were conducted to investigate the influence of carbon ablation on shock layer radiation. Data collected from experiments performed in the X-2 expansion tunnel at the University of Queensland was used to compare to the simulations. The model was made of isomolded graphite and was tested in 8.5 kms Earth entry flow. The model surface was heated within a temperature range of 1770-3280 K. The radiation emitted from the CN violet bands was measured by ultraviolet spectrometry in a spectral range from 353-391 nm. This research develops a novel finite-rate surface kinetic model for determining the chemical state of an ablating boundary layer. The ablative gas species predicted by this new model improves agreement with experimental measurements than predictions provided by legacy ablation models, and represents a significant improvement in current modeling capabilities for hypersonic nonequilibrium ablating re-entry flows.

Subject Categories:

  • Research and Experimental Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE