Publication Date:
2019-08-27
Description:
The effects of boundary layer flows along the walls of wind tunnels were studied to validate the transfer of two dimensional calculations to three dimensional transonic flowfield calculations. Results from trials in various wind tunnels were examind to determine the effects of the wall boundary flow on the control surfaces of an airfoil. Models sliding along a groove in the wall of a channel at sub- and transonic speeds were examined, with the finding that with either nonuniformities in the groove, or even if the channel walls are uniform, the lateral boundary layer can cause variations in the central flow region or alter the onset of shock at the transition point. Models for the effects in both turbulence and in the absence of turbulence are formulated, and it is noted that the characteristics of individual wind tunnels must be studied to quantify any existing three dimensional effects.
Keywords:
AERODYNAMICS
Type:
NASA-TM-77025
,
NAS 1.15:77025
,
ONERA-TP-1981-117
,
Nov 18, 1981 - Nov 20, 1981; Chatillon; France
Format:
application/pdf
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