In actual manuver of an aeroplane, turning flight is accompanied more or less with climbing, as the velocity for most favorable horizontal turn is too small to be actually flown with. For the most simple case of a climbing turn in an inclined plane the author introduced a method of calculation. The climbing turn of an aeroplane was then calculated as an example, taking the angle of inclination of the plane of turning manuver as 15°, 30°, 40°and 45°.
The conclusions are:-
(1) The 180°-turn in an inclined plane in general, needs much shorter time and more narrow space than a horizontal turn, provided the same entering speed and the same maximum load factor.
(2) To obtain the good performance in horizontal turn, the pilot must throtlle the engile and begin the turn with a very low speed. The inclined turn can be entered with much higher speed, and the performance is better than the same as or, at least, the horizontal turn.
(3) In the inclined turn, the aeroplane climbs at first with the excess of power, and when the speed drops, it begins to descend with the result that the speed loss at the end of the 180° turn is much smaller than in the horizontal turn.
(4) For the same load factor, the best performance of the inclined turn is about the same as that of the horizontal one, but the entering speed for the best turn is higher for the former.
(5) The vertical turn cannot be explained as the extreme case of the horizontal turn, since the normal acceleration, i.e. the load factor tends to be infinitely large. Introducing the conception of the turn in an inclined plane, the angle of bank (to the ground) of 90° or more than 90° can be understood as the attitude of the aeroplane at the highest Point in the inclined plane. And, the inclined turn for which the maximum angle of bank reaches about 90° was shown to be the most favorable one for the aeroplane taken as example.
(6) In the inclined turn, as in the horizontal turn, the turning performance becomes better by the use of the wing flap.
(7) The inclined turn is not good for the performance of a continuous turn.

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In der des Verfassers vorigen Arbeit⁽¹⁾ wurde nur eine Form der Druckverteilung uber die Wasseroberfläche angenommen. In der vorliegenden Arbeit werden noch vier andere Formen studiert; rechteckige, dreieckige, sinusförmige und noch eine Kombination der dreieckige und der Verteilung der vorigen Arbeit. Der zweidimensionale Wellenwiderstand von jeder Verteilung wird gerechnet und verglichen. In dem Bereich von der Froudeschen Zahl uber eins stimmen alle Wellenwiderstande anahernd überein.
Der Wellenwiderstand der Tandemgleitflache wird in einem besondern Fall theoretisch behandelt, und wird dem Widerstand der einfachen Gleitflache verglichen. Es wird angedeutet dass der Wellenwiderstand der Tandemgleitflache kleiner werden kann als der der einfachen Gleitfläche.

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本論文は私の卒業論文の一部を拔萃概説したものである.さして重要ならずと思はれる證明はすべて省略し,必要なる結果のみ排列しました.第1章に基礎式を述べ,第2章以下に於て,“周邊自由支持正方形板の大きな撓み”を論じた.第2章一般的考察に於て境界條件及各表示式を述べ,且つ見掛上の剪斷歪は挫屈後に於ける波形の生成に無關係にして,挫屈以前と同じ性質,即ち剪斷荷重に對し直線關係を維持することを證明した.第3章に於て平等法壓力を受けた場合を計算し,第4章で“壓縮板と其の有效幅”について述べ,計算兩場合に於て常に縁材の應力σLの平結果よ一方向壓縮の場合及び2方向等壓縮の方根と平均壓縮力の平方根とが荷重の非常なる廣範圍に及びて殆んど完全に直線關係にあることを發見し,上の結果を近似公式に纒め,更に推理を進めて2方向に働く荷重の比が任意なる場合の式を2種導出し,此等の結果とLahde-Wagnerの實驗結果(1)とを圖に比較した.その結果矩形板の縦横邊長比並びに周邊自由支持固定支持彈性支持の別に依らず一方向壓縮の場合には有效幅とEquivalente σL/σkとは略々同じ關係にあることを主張した.ここにσkは各支持條件に於ける挫屈應力である.最後に同じ問題に對する既出論文との比較をした

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