Experiments on laminar suction wings at Institute for Aerodynamics, Zurich, verified full chord laminar flow and low wing profile drags by means of suction up to Re 2.5×106 wing chord; to investigate behavior at reduced turbulence level, corresponding to flight conditions, 15%-thick slotted low drag suction wing model was tested in Langley Field TDT tunnel; for comparison, Zurich BLC results and profile drags of various non-suction wings are presented with laminar and turbulent friction drag of flat plates.
Recent developments in field of low drag boundary layer suction research
AGARD -- Report
1960
26 pages
Report
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Optimum drag balance for boundary-layer suction
AIAA | 1996
|Optimum Drag Balance for Boundary-Layer Suction
Online Contents | 1996
|Theoretical investigation of drag reduction by maintaining laminar boundary layer by suction
Engineering Index Backfile | 1947
|Gradient effects on drag due to boundary-layer suction in automotive wind tunnels
Tema Archive | 2003
|