Preliminary airfoil testing experience in the NDA cryogenic wind tunnel

Author

Yamaguchi, Yutaka ; Nakauchi, Yasuo ; Yorozu, Masahiro ; Saito, Teruo

Author_Institution

Nat. Defense Acad., Yokosuka, Japan

fYear

1991

fDate

27-31 Oct 1991

Firstpage

223

Lastpage

230

Abstract

A small two-dimensional high-speed cryogenic wind tunnel was constructed at the Japanese National Defense Academy (NDA) in 1985. The authors describe the present status of the NDA cryogenic wind tunnel and give some preliminary airfoil testing results and experience. Two airfoil models, a NACA 0012 and a R4 airfoil model, were constructed. The R4 test results were compared with those of NASA TM-85739. They were in good agreement in the negative angle of attack range. However, the present R4 model has an extremely small aspect ratio of 0.5 and a high section thickness to tunnel height ratio of about 0.1. Therefore, the present results might be more influenced by the tunnel walls than those of NASA

Keywords

aerospace testing; wind tunnels; Japanese National Defense Academy; NACA 0012; NDA cryogenic wind tunnel; R4 airfoil model; airfoil testing; data acquisition; Automatic control; Automotive components; Circuit testing; Cryogenics; Electric motors; NASA; Pi control; Pressure control; Proportional control; Valves;

fLanguage

English

Publisher

ieee

Conference_Titel

Instrumentation in Aerospace Simulation Facilities, 1991. ICIASF '91 Record., International Congress on

Conference_Location

Rockville, MD

Type

conf

DOI

10.1109/ICIASF.1991.186243

Filename

186243