Abstract
A PRELIMINARY numerical characterization of a U.S. Air Force Research Laboratory (AFRL) test facility was performed. Research cell 22 (RC22) is a supersonic wind-tunnel facility at AFRL. RC22 is presently simulating dual-mode combustion for circular (axisymmetric) combustors. Previous efforts in RC22 have studied combustion in rectangular flowpaths. The current effort in RC22 is to examine the benefits of axisymmetric flowpaths as compared with rectangular. For the same cross-sectional area in which circular flowpaths eliminate the challenges involved with corner flow effects, they have increased structural efficiency (heat load distribution) and have reducedweight. Circular combustors also pose challenges that involve effective fuel penetration and flame propagation. For more information regarding the rectangular experiments performed in RC22, refer to [1].
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