@article{hollis_perkins_1999, title={Transition effects on heating in the wake of a blunt body}, volume={36}, ISSN={["0022-4650"]}, DOI={10.2514/2.3499}, abstractNote={A series of aerodynamic heating tests was conducted on a 70-deg sphere-cone planetary entry vehicle model in a Mach 10 perfect-gas wind tunnel at freestream Reynolds numbers based on diameter of 8.23x104 to 3.15x105. Surface heating distributions were determined from temperature time-histories measured on the model and on its support sting using thin-film resistance gages. The experimental heating data were compared to computations made using an axisymmetric/2D, laminar, perfect-gas Navier-Stokes solver. Agreement between computational and experimental heating distributions to within, or slightly greater than, the experimental uncertainty was obtained on the forebody and afterbody of the entry vehicle as well as on the sting upstream of the free-shear-layer reattachment point. However, the distributions began to diverge near the reattachment point, with the experimental heating becoming increasingly greater than the computed heating with distance downstream from the reattachment point. It was concluded that this divergence was due to transition of the wake free shear layer just upstream of the reattachment point on the sting.}, number={5}, journal={JOURNAL OF SPACECRAFT AND ROCKETS}, author={Hollis, BR and Perkins, JN}, year={1999}, pages={668–674} }
 @article{hollis_perkins_1997, title={High-enthalpy aerothermodynamics of a Mars entry vehicle .2. Computational results}, volume={34}, ISSN={["0022-4650"]}, DOI={10.2514/2.3258}, abstractNote={Numerical solutions for hypersonic  ows of carbon dioxide and air around a 70-deg sphere–cone Mars entry vehicle conŽ guration were computed using a laminar, axisymmetric, nonequilibrium Navier–Stokes solver with freestream  ow conditions equivalent to those of aerothermodynamic tests conducted in a high-enthalpy impulse facility. The wake  owŽ eld computations were found to be much more sensitive to both grid resolution and grid adaptationthan the forebody results. The wake computations showed the existence of a region of separated, steady, recirculating  ow behind the vehicle. Whereas the rapid expansion of the  ow around the corner of the vehicle resulted in a wake that was mostly frozen both chemically and vibrationally, the degree of  ow expansion was not great enough to produce noncontinuum ow behavior. Comparisons between computational and experimental surface heating distributionswere within the estimated experimental uncertainty for both cases except around the forebody stagnation point and the free-shear-layer reattachment point for the air case and within a small portion of the wake recirculation vortex for the carbon dioxide case.}, number={4}, journal={JOURNAL OF SPACECRAFT AND ROCKETS}, author={Hollis, BR and Perkins, JN}, year={1997}, pages={457–463} }
 @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} }