The Experimental Investigation of HLFC-System Use on the Swept Wing at Subsonic Velocities

975500

10/01/1997

Event
World Aviation Congress & Exposition
Authors Abstract
Content
Carried out in the TsAGI T-107 subsonic wind tunnel (test section diameter dw.t. = 2.7 m.) has been the experimental investigation of subsonic flow -9.4·106) about a large-scale half-model (span 1.67 m, chord 0.73 m) of a swept untapered wing (χ = 35°, η = 1, = 9.8%) equipped with a local boundary-layer suction system . Based on a measured pressure distributions, angles of attack were selected (α = -2° and -4°) to be rational from the standpoint of cross-flow disturbance's development. The extent of the laminar flow zone was determined through various methods. Based on the losses of the total pressure measured in the wake behind the mid-section of the swept portion of the model, the decrease in the section drag was estimated due to local boundary-layer suction. Several laws and suction rates as well as the chordwise extents of the suction region were tested with the aim of obtaining a maximum decrease in the section drag of the swept wing.
Meta TagsDetails
DOI
https://doi.org/10.4271/975500
Pages
9
Citation
Bokser, V., Babuev, V., Kiselev, A., Mikeladze, V. et al., "The Experimental Investigation of HLFC-System Use on the Swept Wing at Subsonic Velocities," SAE Technical Paper 975500, 1997, https://doi.org/10.4271/975500.
Additional Details
Publisher
Published
Oct 1, 1997
Product Code
975500
Content Type
Technical Paper
Language
English