Base bleed experiments with a cylindrical afterbody in supersonic flow

T. Mathur, J. C. Duttont

Research output: Contribution to conferencePaperpeer-review


The effect of base bleed on the near-wake flowfield of a cylindrical afterbody aligned with a Mach 2.5 flow has been investigated. This study is aimed at better understanding the complex fluid dynamic interactions occurring in the near-wake due to base bleed and is motivated by the lack of detailed velocity and turbulence data in this flowfield The experimental techniques used include static pressure measurements along the afterbody and the base plane, schlieren and shadowgraph photography, and centerline traverses using two-component laser Doppler velocimetry (LDV). Results indicate relatively uniform radial pressure profiles across the base plane. With increasing bleed flowrate (quantified by the injection parameter, I), the average base pressure is found to increase initially, attain a peak value near I = 0.0148, and then decrease with further increase in I. The optimum bleed condition near I = 0.0148 is also characterized by a weak comer expansion, a minimum value of the free shear layer angle, and the near-disappearance of the recirculation region (reverse velocity) along the centerline of the near-wake.

Original languageEnglish (US)
StatePublished - 1995
Event33rd Aerospace Sciences Meeting and Exhibit, 1995 - Reno, United States
Duration: Jan 9 1995Jan 12 1995


Other33rd Aerospace Sciences Meeting and Exhibit, 1995
Country/TerritoryUnited States

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering


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