Preliminary airfoil testing experience in the NDA cryogenic wind tunnel

Yamaguchi, Yutaka; Nakauchi, Yasuo; Yorozu, Masahiro; Saito, T.

doi:10.1109/iciasf.1991.186243

Cited by 6 publications

(2 citation statements)

References 3 publications

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“…For airfoil printing, the ratio of airfoil length and chord length is accepted as 1/1. The airfoil mass was manufactured as 348,21 g, volume as 341379,35 mm 3 and surface area as 54582 mm 2 .…”

Section: Experimental Studies and Evaluationmentioning

confidence: 99%

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Positioning analysis of the lift force sensor in subsonic wind tunnel test chamber design and its effect on naca0015 airfoil

TUNCA,

ÖZGÜR

2023

JSR-A

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In this study, analysis was carried out by placing the force sensor in different positions in the subsonic wind tunnel test room. NACA0015 profile was used as the airfoil. The model used in the open system subsonic wind tunnel with a 50x50 cm test chamber was manufactured by 3D printing method. Lift force (CL) measurements were studied at Reynolds number (Re) values of 60000, 80000 and 100000. Measurements were analyzed in one-degree increments of the angle of attack, starting from 00. The force device is positioned in 4 different ways around the test room. Efficient results could not be obtained in 3 of the connection attempts. The reason why the results are not efficient is that the fasteners are incompatible with the airfoil, force device and system. The incompatibility of the fasteners caused vibration and a negative situation in the airfoil. There is a slope in the connection made from the side. As a result of the slope, the airfoil has deteriorated. It was observed that the measurements made by positioning the force device inside the test chamber were compatible with the literature. The resulting graph shows an approach to the literature. Although it is graphically compatible, it should be noted that there is a deviation of approximately 10% in the data. Connection stiffness is gaining importance. It has been observed that stall begins at angles of approximately 100 and 110 degrees.

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Section: Experimental Studies and Evaluationmentioning

confidence: 99%

“…Regarding wind tunnel manufacturing studies, a small, two-dimensional, high-speed cryogenic wind tunnel was built at the Japanese National Defense Academy (NDA) in 1985. R4 airfoil test results in the NDA cryogenic wind tunnel were compared to those of NASA TM-85739 [2].…”

Section: Introductionmentioning

confidence: 99%