高速流中に於ける翼型の抵抗

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The momentum method of measuring the resistance of body was applied to NACA-4412 aerofoil placed in 36cm high speed tunnel of the institute. The method is a modification of that of Bicknell taking into consideration the change of temperature in the wake. At highest speed of the tunnel remarkable degree of the gradient of static pressure was present due to the mutual interference of tunnel wall. Even in this case the resistance could be calculated taking into consideration the difference of the static pressure, and taking the momentum equation in its original form. The aerofoil, 75mm in chord, was so placed as to traverse the stream from wa 〓 to wall. The exploring pitot and static tube were 1mm in diameter and were placed side by side. They were attached to a carriage which was able to change the position in the stream as required. The result of the experiment is shown in Fig.16 together with the drag coefficient obtained in NACA high speed tunnel. The drag curve of the present experiment lies in the midway between the curves obtained from force and pressure tests at NACA. The authors explored the velocity distribution near the aerofoil with pitot and static tubes and came to the conclusion that the shock wave does not start necessarily at the moment when the local velocity of sound is attained as is generally believed. In fact, the shock wave was noted to start only when the local velocity of sound is somewhat exceeded, although the drag coefficient begins to increase earlier just at the local velocity of sound. The exploration of velocity field led the authors to construct the shock waves as shown in Fig.29 and 30. The position and the configuration of the shock wave are very similar to the american experiments.
宇宙航空研究開発機構の論文

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河曲三治
東京大學理工學研究所

高速流中に於ける翼型の抵抗

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