Study of the influence of a highly integrated flow-through intake on compressible flows about the lambda wing configuration SACCON

Abstract

The influence of a highly integrated flow-through intake on the vortical flow around the SACCON configuration is studied for 0.55·10^6< Re < 2.45·10^6 and 0.3 < M < 0.75. To this end, two versions of the SACCON configuration are considered, the original one without an intake, and a modified one with intake and exhaust openings on the lee side. Experimental investigations were performed in the transonic wind tunnel DNW-TWG. Forces and moments were measured by a strain gauge balance and the pressure distribution on the lee side of the model was determined by pressure sensitive paint (PSP). An estimate of the non-dimensional mass flux through the intake is obtained from direct pressure measurements within the ducts. The experimental tests are supplemented by numerical investigations performed for two Mach numbers. The effect of the intake is discussed by comparing results obtained for the two versions of the model under otherwise same conditions.