NASA NTRS · 19830018567
Dynamic Distortion in a Short S-Shaped Subsonic Diffuser with Flow Separation
Abstract
An experimental investigation of the time varying distortion at the diffuser exit of a subscale HiMAT forebody and inlet was conducted at Mach 0.9 in the Lewis 8 by 6 foot Supersonic Wind Tunnel. A transitory separation was detected within the subsonic diffuser. Vortex generators were installed to eliminate the flow separation. Results from a study of the instantaneous pressure variations at the diffuser exit are presented. The time unsteady total pressures at the diffuser exit are computer interpolated and presented in the form of a movie showing the transitory separation. Limited data showing the instantaneous distortion levels is also presented.
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Stumpf, R., Neumann, H. E., Giamati, C. C.. 1983-01-01. Dynamic Distortion in a Short S-Shaped Subsonic Diffuser with Flow Separation. https://ntrs.nasa.gov/citations/19830018567
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