Some observations of flow at the throat of a two-dimensional diffuser at a Mach number of 3.85

James F. Connors, Richard R. Woolett
naca-rm-e52i04
Nov 1952


An experimental investigation was conducted at a Mach number of 3.85 in the Lewis 2- by 2-foot supersonic wind tunnel to study the flow patterns at the throat of a two-dimensional single-shock diffuser and to evaluate qualitatively several schemes for improving the turning conditions. Schlieren observations were made for supercritical inlet operation and for conditions of maximum total-pressure recovery. The angle of attack of the model was limited to zero.

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