TY - GEN
T1 - Freestream disturbance effects on boundary layer instability and transition on the afosr bolt geometry
AU - Kostak, Heather E.
AU - Bowersox, Rodney D.W.
AU - McKiernan, Gregory R.
AU - Thome, John
AU - Candler, Graham V.
AU - King, Rudolph A.
PY - 2019/1/1
Y1 - 2019/1/1
N2 - The Air Force Office of Scientific Research (AFOSR) introduced the Boundary Layer Transition (BOLT) flight experiment to assess modern prediction via simulation and ground test. The BOLT test article is a new, complex geometry that involves concave surfaces with highly swept leading edges. This paper compares preliminary results on the same subscale model tested in four hypersonic wind tunnel facilities. Tests were performed in the Boeing/AFOSR Mach 6 Quiet Tunnel at Purdue University, the conventional 20-inch Mach 6 Air tunnel at NASA Langley Research Center, and the conventional ACE and Mach 6 Quiet wind tunnels at Texas A&M University. The measurements across the facilities included thermal imaging and surface mounted high-frequency pressure transducers. University of Minnesota’s CFD analyses of the BOLT geometry were compared to the quiet flow facilities. Systematic similarities and differences were observed in terms of surface heating, stationary streaks, and modal growth.
AB - The Air Force Office of Scientific Research (AFOSR) introduced the Boundary Layer Transition (BOLT) flight experiment to assess modern prediction via simulation and ground test. The BOLT test article is a new, complex geometry that involves concave surfaces with highly swept leading edges. This paper compares preliminary results on the same subscale model tested in four hypersonic wind tunnel facilities. Tests were performed in the Boeing/AFOSR Mach 6 Quiet Tunnel at Purdue University, the conventional 20-inch Mach 6 Air tunnel at NASA Langley Research Center, and the conventional ACE and Mach 6 Quiet wind tunnels at Texas A&M University. The measurements across the facilities included thermal imaging and surface mounted high-frequency pressure transducers. University of Minnesota’s CFD analyses of the BOLT geometry were compared to the quiet flow facilities. Systematic similarities and differences were observed in terms of surface heating, stationary streaks, and modal growth.
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U2 - 10.2514/6.2019-0088
DO - 10.2514/6.2019-0088
M3 - Conference contribution
SN - 9781624105784
T3 - AIAA Scitech 2019 Forum
BT - AIAA Scitech 2019 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Scitech Forum, 2019
Y2 - 7 January 2019 through 11 January 2019
ER -