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Venkatapathy, E., Laub, B., Hartman, G J., Arnold, J.O., Wright, M.J. and Allen, G.A. (2009) Thermal Protection System Development, Testing, and Qualification for Atmospheric Probes and Sample Return Missions. Examples for Saturn, Titan and Stardust-Type Sample Return. Advance in Space Research, 44, 138-150.
https://doi.org/10.1016/j.asr.2008.12.023

has been cited by the following article:

• TITLE: Nose-Tip Transition Control by Surface Roughness on a Hypersonic Sphere

  AUTHORS: Kiran Joy Irimpan, Viren Menezes, K. Srinivasan, Hamid Hosseini

  KEYWORDS: Shock Tunnel, Hypersonic, Transition, Surface Roughness, Thermocouple

  JOURNAL NAME: Journal of Flow Control, Measurement & Visualization, Vol.6 No.3, June 29, 2018

  ABSTRACT: The surface heat flux on a 100 mm diameter hypersonic sphere was reduced through surface roughness on its forebody. The test model was subjected to a hypersonic freestream of Mach 8.8 and Reynolds number 1.98 million/m, in a shock tunnel. Forebody surface heat transfer rates measured on smooth and rough spheres, under the same free-stream conditions, were compared. The comparison of heat flux indicated an overall reduction in surface heating rates on the rough model, which could be attributed to the delayed nose tip transition. The surface roughness on the forebody of the model generated miniature cavities. Stability of the free shear layer over the miniature cavities and entrapment of the destabilizing vortices in the cavities, make the flow over the rough test model more stable than the attached boundary layer over the smooth model, under transitional conditions.