Transition on Hypersonic Vehicles with Crossflow
Technical Report,01 Jul 2015,01 Jul 2017
Hypersonic Sciences Branch Wright-Patterson Air Force Base
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This interim technical report summarizes technical activity on AFRL 6.1 laboratory task LRIR 15RQCOR102 during fiscal year 2017. The objective of this task is to better understand boundary layer transition in hypersonic flowfields with spanwise nonuniformity. Several advances were made under this task during FY17. The HIFiRE-5b flight data were analyzed. Wind tunnel tests were conducted at angles of attack and yaw representative of flight, and computations were carried out for the flight conditions. Also, analysis of cones at angle of attack, as tested in the AFRL Mach 6 high Reynolds number wind tunnel, was also conducted. The effects of angle of attack and yaw angle on crossflow transition on the test bodies were quantified. Multiple transition effects arising from crossflow modes, attachment-line and centerline traveling instabilities were identified. These transition mechanisms were identified by their peculiar transition patterns and behaviors in flight, wind tunnel and computations. Generally, the Parabolized Stability Equations were effective in predicting crossflow and attachment line transition behavior.
- Fluid Mechanics