Observation and analysis of sidewall effect in a transonic airfoil test section

Author

Yaoxi, Su ; Puffert-Meißner, W.

Author_Institution

NPU Xian, China

fYear

1989

fDate

18-21 Sep 1989

Firstpage

50

Lastpage

56

Abstract

Oil flow tests were conducted to investigate the sidewall effect in transonic airfoil testing. Features of each type of flow pattern are described. It is found that the flow pattern develops systematically with the increase of Mach number and the angle of attack as a result of the development of sidewall effects. The sidewall effects of supercritical flow are found to be very different from those of subcritical flow and have a more pronounced influence on the measurements. Different hypotheses on the principle of sidewall effects are discussed. It is suggested that the sidewall effects are mainly caused by the displacement effect of the sidewall boundary layer

Keywords

aerospace testing; boundary layers; flow measurement; transonic flow; Mach number; angle of attack; displacement effect; flow pattern; oil flow test; sidewall boundary layer; sidewall effect; subcritical flow; supercritical flow; transonic airfoil test; Automotive components; Electric shock; Fluid flow measurement; Interference; Petroleum; Scattering; Shock waves; Testing; Uncertainty; Visualization;

fLanguage

English

Publisher

ieee

Conference_Titel

Instrumentation in Aerospace Simulation Facilities, 1989. ICIASF '89 Record., International Congress on

Conference_Location

Gottingen

Type

conf

DOI

10.1109/ICIASF.1989.77658

Filename

77658