著者

安東 茂典

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.129, pp.347-364, 1964 (Released:2009-05-25)

著者

安東 茂典

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.35, no.397, pp.91-101, 1987-02-05 (Released:2010-12-16)

参考文献数

12

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A concept of PAR (Power Augmented Ram Wing) is presented. It will be useful in future for over-water transport vehicles to carry passengers, cargos, and/or cars. It is much faster than ships, while it requires no run-way in contrast to airplanes. The PAR concept makes the fuselage-shape “aero-configured” rather than “hydro-configured”, and so decreases the parasite-drag singificantly. An empirical formula is found for the effective aspect ratio which is applicable to verious kinds of Ground Effect Wings. The present PAR concept has a variable geometry wing, in front of which tiltable turboprop engines are installed. Untill the take-off speed is exceeded, the wing is swept-forward with extended full span flaps (the outer ones are differential flaps). In cruising condition the wing becomes unswept. If the sea-state is bad the vehicle can fly off-ground effect with unswept wing. Thus cancelling operations is much more reduced than hovercrafts or hydrofoil-boats. Special devices are proposed for the tip-floats, which improve aero-dynamic efficiency and which alleviate load due to wave-impacts.

著者

安東 茂典 西脇 英彦

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.19, no.207, pp.148-154, 1971 (Released:2009-05-25)

参考文献数

7

著者

安東 茂典 梶田 弘

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.40, no.456, pp.14-22, 1992

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Static longitudinal stability of tailless airplane is evaluated theoretically with two methods. One is quasi (or modified)-strip method and the other is a lifting surface theory—DLM. Computation is made on the basis of available data of Northrop XB-35. The both methods agree each other only qualitatively; of course results of DLM should be much more reliable. Allowable limit of longitudinal CG position may be almost comparable with that of conventional airplanes. The airplane efficiency factor, e concerning with induced drag, is computed which is also satisfactory at least for cruising configuration.

著者

安東 茂典 梶田 弘

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.40, no.456, pp.14-22, 1992-01-05 (Released:2010-12-16)

参考文献数

13

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Static longitudinal stability of tailless airplane is evaluated theoretically with two methods. One is quasi (or modified)-strip method and the other is a lifting surface theory—DLM. Computation is made on the basis of available data of Northrop XB-35. The both methods agree each other only qualitatively; of course results of DLM should be much more reliable. Allowable limit of longitudinal CG position may be almost comparable with that of conventional airplanes. The airplane efficiency factor, e concerning with induced drag, is computed which is also satisfactory at least for cruising configuration.

著者

安東 茂典 加藤 三千代

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.39, no.455, pp.675-679, 1991-12-05 (Released:2010-12-16)

参考文献数

4

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A quick automatic method is presented for computing performance of nonducted propeller with constant revolutional speed. This study is motivated by usefulness for developing WIG vehicles, namely in order to predict propeller data to be used. Results of computation examples show that constant-speed-propellers are considerably robust, viz. insensitive to change of some parameters such as diameter, solidity and rotational speed. It is noteworthy that these well-known properties are confirmed easily and quickly by the present method.

著者

安東 茂典

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.46, no.532, pp.289-295, 1998-05-05 (Released:2010-12-16)

参考文献数

6

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This paper is an important supplement of the previous one, titled as “A systematic computation scheme for PAR-WIG cruising design point.” The motive is one point—upper limit of aspect ratio of WIG main wing on which sufficient PAR effect can appear at take-off. Previously this fact was described only qualitatively without any FORTRAN computation, and thus aspect ratio of 6.0 was recommended somewhat arbitrarily. The main purpose of this paper is to clarify this point. Accompanying this, some other requirements on geometry of main wing of WIG are obtained.