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.