Accession Number : ADA623564


Title :   HIFiRE-5 Boundary Layer Transition and HIFiRE-1 Shock Boundary Layer Interaction


Descriptive Note : Interim rept. 31 Oct 2014-15 Oct 2015


Corporate Author : AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AEROSPACE SYSTEMS DIRECTORATE


Personal Author(s) : Kimmel, Roger L ; Borg, Matthew P ; Jewell, Joseph S ; Miller, James H ; Prabhu, Dinesh


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a623564.pdf


Report Date : Oct 2015


Pagination or Media Count : 68


Abstract : Several advances were made under this task during FY15, the first year of this effort. A portion of the task effort focused on HIFiRE-5. For this work, new capabilities in ground test and in flight data analysis were developed. Also, as a necessary precursor to wind tunnel tests on boundary layer transition on the leeside of a cone at angle of attack, extensive computations were undertaken to understand the zero angle of attack instability behavior. Although not directly related to the topic of boundary layer transition, final analysis of the HIFiRE-1 shock boundary layer interaction experiment was completed.


Descriptors :   *BOUNDARY LAYER TRANSITION , ANGLE OF ATTACK , CROSS FLOW , FLIGHT TESTING , HEAT TRANSFER , INFLIGHT , INFRARED IMAGES , INSTABILITY , MACH NUMBER , PRECURSORS , WIND TUNNEL TESTS


Subject Categories : Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE