Generic Lambda Wing Configuration in Compressible Flow: Effect of Highly Integrated Intakes

Abstract

The influence of a highly integrated flow-through intake on the vortical flow about a generic lambda wing configuration is studied for 0.55 · 106 < Re < 2.45 · 106 and 0.3 < M < 0.75. To this end, two versions of the configuration are considered: a clean one without intake, and a modified one with intake and exhaust openings on the lee side. Experimental investigations were performed in the transonic wind tunnel Göttingen of the German–Dutch Wind Tunnels. 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. An estimate of the nondimensional 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.