著者
山名 正夫
出版者
一般社団法人 日本航空宇宙学会
雑誌
日本航空学会誌 (ISSN:00214663)
巻号頁・発行日
vol.2, no.6, pp.108-112, 1954-03-31 (Released:2009-07-09)
参考文献数
3

Some of the wartime Japanese navy planes at their experimental stages were easily brought into accidental (or unintentional) autorotation in acrobatic flight such as vertical turn or loop. The analytical studies, refining procedures taken against these defects and design precautions are described here.When the wing is liable to stall at its tip or at the approximate middle portion between tip and root, and when the directional stability is not sufficient under large incidence angles, the accidental autorotation will happen due to small side slip angle ψ or angular velocity r around Z axis caused by a slight and unavoidable incoordination of control. The procedures are indicated in Fig. 5.Consequently it is summarized: that the stall of main wing should grow gradually outward from root and forward from trailing edge as indicated in the right half of Fig. 6 (a), that the value of ∂Cn/∂ψ should not decrease even under large incidence angles.
著者
堀越 二郎
出版者
一般社団法人 日本航空宇宙学会
雑誌
日本航空学会誌 (ISSN:00214663)
巻号頁・発行日
vol.15, no.158, pp.78-90, 1967-03-05 (Released:2009-07-09)
参考文献数
8

The author conceived that "control force vs. response" should be extended to "control force and displacement vs. response" in order to assure average pilots of safer, easier, and more precise flying of airplanes with wide speed range. Stick displacement per response varies inversely proportional to speed squared, unless dynamic pressure effect is compensated. The author tried to realize this concept by a deliberate reduction of elevator control system stiffness, which would almost ideally shift upward and flatten the curves of stick displacement per response vs. speed over a wide range of speed. Proper pilot-airplane matching is most seriously needed in longitudinal control. The concept and method proposed were verified by flight tests 27 years ago and applied to three models of airplanes, including the Zero Fighter. This paper describes how the afore-mentioned concept and idea were born and proved, and deals with the demonstration of their effects by theoretical analyses and by comparison of the results of numerical calculations with those of the flight tests, and with counterproofs against apprehensions for adverse effects. It is pointed out that the method is applicable to normally designed subsonic airplanes and is especially effective for those operated over wide ranges of speed and normal acceleration. Comparison is made with the results of recent research.
著者
疋田 遼太郎 武田 峻 市川 輝雄 田辺 哲夫 馬場 敏治 檜山 斉雄 得能 健次郎
出版者
一般社団法人 日本航空宇宙学会
雑誌
日本航空学会誌 (ISSN:00214663)
巻号頁・発行日
vol.2, no.10, pp.255-263, 1954-10-31 (Released:2009-07-09)

The aircraft Model FD-25 A is a trainer manufactured by the TOYO-KOKU-KOGYO Ltd., with the design of the Fletcher Aircraft Corp. To demonstrate the strength of this aircraft, the load was applied under a system of forces simulating as closely as possible those required in the regulation of C.A.A. of Japan. In this paper, the result of tests, the method of load calculation and the loading apparatus were reported and discussed.
著者
平木 敏夫
出版者
一般社団法人 日本航空宇宙学会
雑誌
日本航空学会誌 (ISSN:00214663)
巻号頁・発行日
vol.12, no.125, pp.198-204, 1964 (Released:2009-05-25)

To improve helicopter performance, there are four problems to be solved, i.e. engine power-up, drag reduction, retreating blade stall prevention and prevention of compressibility phenomena on advancing blade.To solve above problems, in this paper, various methods with constant speed rotor are compared by analyses and wind tunnel tests.As the results, feasibility of 180 knot helicopter, a compound type helicopter withfixed-wing thrustpropeller, will be justified.