@article{bynum_hollis_hassan_xiao_2008, title={Turbulent aeroheating on the mars science laboratory entry vehicle}, volume={22}, ISSN={["1533-6808"]}, DOI={10.2514/1.33281}, abstractNote={A series of calculations are carried out for a Mars Science Laboratory entry vehicle heat shield and compared with tests carried out in the Arnold Engineering Development Center for Mach 8 and 10 and a range of Reynolds numbers. Three turbulence models are employed that are implemented in the LAURA code: the Cebeci-Smith algebraic model, the 98 Wilcox k − ω model, and the k − ζ model. In general, good agreement is indicated with turbulent predictions. Because the flow is attached, the algebraic model performs as well as other models.}, number={2}, journal={JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER}, author={Bynum, Michael D. and Hollis, Brian R. and Hassan, H. A. and Xiao, X.}, year={2008}, pages={306–309} }
 @article{nance_hollis_horvath_alter_hassan_1999, title={Computational study of hypersonic transitional wake flow}, volume={13}, ISSN={["1533-6808"]}, DOI={10.2514/2.6441}, abstractNote={A study of transition and turbulence in hypersonic blunt-body wake flows is presented. The current approach combines the A>£ turbulence closure model with a newly developed transition prediction method. This method utilizes results from linear stability theory and treats transitional flows in a turbulence-like manner. As a result, the onset and extent of transition are determined as part of the solution. The model is used to study flows past two spherically blunted 70-deg cone geometries at Mach 6 and 10. Two mechanisms of instability are examined. Comparison between computation and experiment suggests that for the cases considered, transition is a result of the instability of the free shear layer emanating from the shoulder region.}, number={2}, journal={JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER}, author={Nance, RP and Hollis, BR and Horvath, TJ and Alter, SJ and Hassan, HA}, year={1999}, pages={236–242} }
 @article{hollis_perkins_1997, title={High-enthalpy aerothermodynamics of a Mars entry vehicle part .1. Experimental results}, volume={34}, ISSN={["0022-4650"]}, DOI={10.2514/2.3257}, abstractNote={Aerodynamic heating tests were conducted on a 70-deg sphere ‐cone Mars entry vehicle cone guration in a high-enthalpy impulse facility in both carbon dioxide and air test gases. The purpose of these tests was to obtain heat transfer data for comparison with results of Navier ‐Stokes computations. Surface heat transfer rates were determined for both the forebody and afterbody of the test models and for the stings that supported the models in the facility test section. Little difference was observed between normalized heating distributions for the air and carbon dioxide test conditions. For both cases, peak sting heating was on the order of 4 ‐5% of the forebody stagnation-point heating, and it was concluded that the wake e ow remained laminar. The wake e ow establishment process was quantie ed and was found to require approximately 40 ‐70 e ow path lengths, which corresponded to approximately 75% of the available facility test time. The repeatability of facility test conditions was estimated to vary between § 3% and § 10%. The overall experimental uncertainty of the data was estimated to be § 10‐11% for forebody heating and § 17‐22% for wake heating.}, number={4}, journal={JOURNAL OF SPACECRAFT AND ROCKETS}, author={Hollis, BR and Perkins, JN}, year={1997}, pages={449–456} }