Abstract: A laminar flow control arrangement for use in a nacelle for an aircraft turbine engine. The nacelle has a microporous outer skin in the area where air flow over the skin is to be maintained in laminar flow. A honeycomb core is bonded to the inner surface of the nacelle skin. A perforated back skin is bonded to the inner surface of the core. Several closely spaced circumferential flutes open to the back skin are fastened to the back skin. At least one collector duct is connected to the flutes and a suction pump. In operation, the suction pump pulls air through the ducts and flutes, causing air to be sucked inwardly through the microporous skin thereby maintaining laminar, rather than turbulent, flow over a large part of the nacelle during aircraft take-off and cruise operation. In addition, a chamber is preferably provided in communication with any gaps in the nacelle skin in the area where laminar flow is desired.