An experimental and analytical study of flow through a supersonic open channel with contoured floorA wind tunnel experiment was performed to study the characteristics of supersonic airflow (M(infinity) = 2.5-3.86) through an open channel with a contoured floor. The measured static pressures along the centerline of the channel floor exhibited an unexpected rise at the end of the channel. Complex three-dimensional interactions of compression and expansion waves within the channel coupled with external flow perturbations caused by model/tunnel wall interference were the suspected sources of this flow behavior. Three-dimensional inviscid flow analysis procedures were used to investigate and explain this phenomenon. The results of the computations and the experiment are presented and discussed.
Document ID
19840054842
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Saheli, F. P. (Boeing Aerospace Co. Seattle, WA, United States)
Dunn, B. (Boeing Aerospace Co. Seattle, WA, United States)
Marrs, K. (Boeing Aerospace Co. Seattle, WA, United States)
Kumar, A. (NASA Langley Research Center Hampton, VA, United States)
Peery, K. M. (AMTEC Engineering, Inc. Bellevue, WA, United States)