English

DTIC ADA138865: An Experimental and Analytic Study of the Flow Subsonic Wind Tunnel Inlets.

This report documents an experimental and numerical study of the aerodynamic behavior of three dimensional subsonic wind tunnel inlets. The purpose of the study was to develop a rational procedure for the aerodynamic design of high contraction ratio, subsonic wind tunnel inlets. Of particular concern were those factors associated with the inlet design which would influence the use of smoke flow visualization techniques. This three-phased study included the following tasks: (1) The development and assessment of aerodynamic calculation techniques suitable for subsonic wind tunnel inlet flow-field predictions. Both a surface panel technique and a finite difference field solution were developed. (2) The design and fabrication of an indraft tunnel inlet which could be used to visualize the flow within the inlet. (3) The development of design criteria based on the numerical prediction techniques for three dimensional inlets with contraction ratios in a range of 10-40. Four basic parameters were used to characterize the inlet flow fields and a series of design charts are presented for matched cubic wall geometries.

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