The Experimental Investigation of HLFC-System Use on the Swept Wing at Subsonic Velocities 975500
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, c̄ = 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.
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. Download Citation
V. D. Bokser, V. Babuev, A. Kiselev, V. G. Mikeladze, G. K. Shapovalov
World Aviation Congress & Exposition
SAE 1997 Transactions - Journal of Aerospace-V106-1