Print Email Facebook Twitter Low speed windtunnel measurements on a two-dimensional flapped wing model using tunnel wall boundary layer control at the wing-wall junctions Title Low speed windtunnel measurements on a two-dimensional flapped wing model using tunnel wall boundary layer control at the wing-wall junctions Author de Vos, D.M. Institution National Aerospace Laboratory NLR Date 1973-04-09 Abstract An investigation on a two-dimensional wing model with a double-slotted trailing edge flap is described where tunnel wall boundeo'y layer control by blowing was applied to prevent premature flow separations at the junctions between the model and the tunnel walls. From the results it is concluded that tunnel wall boundary layer control at the wall junctions is necessary to obtain useful results from two-dimensional high-lift tests in windtunnels. It is shown that a relatively simple system of compressed air blowing slots in the tunnel walls gives a sufficient approximation of the desired two-dimensional flow pattern. The blowing system has already been applied on a routine basis to wing sections with trailing edge and also leading edge high-lift devices. Subject windtunnel testing techniquetwo-dimensional high lift mogelsblowing boundary layer control on tunnelwalls To reference this document use: http://resolver.tudelft.nl/uuid:9ede41e8-a4c4-4212-a2b1-3c21dbea20e3 Publisher Nationaal Lucht- en Ruimtevaartlaboratorium Access restriction Campus only Source NLR-TR 70050 U Part of collection Aerospace Engineering Reports Document type report Rights (c) 1973 National Aerospace Laboratory NLR Files PDF NLR_TR_70050_U.pdf 22.21 MB Close viewer /islandora/object/uuid:9ede41e8-a4c4-4212-a2b1-3c21dbea20e3/datastream/OBJ/view