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超音速自由飛行試験法による飛しょう体の空力特性の研究
https://jaxa.repo.nii.ac.jp/records/45134
https://jaxa.repo.nii.ac.jp/records/4513421b21187-a0cb-490d-957a-0ae465ab369b
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr00876.pdf (12.7 MB)
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| Item type | テクニカルレポート / Technical Report(1) | |||||||||
|---|---|---|---|---|---|---|---|---|---|---|
| 公開日 | 2015-03-26 | |||||||||
| タイトル | ||||||||||
| タイトル | 超音速自由飛行試験法による飛しょう体の空力特性の研究 | |||||||||
| 言語 | ||||||||||
| 言語 | jpn | |||||||||
| 資源タイプ | ||||||||||
| 資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||||||
| 資源タイプ | technical report | |||||||||
| その他のタイトル（英） | ||||||||||
| その他のタイトル | Research on the Aerodynamic Characteristics of Vehicles by Free Flight Testing at Supersonic Speeds | |||||||||
| 著者 |
河本, 巌
× 河本, 巌
× KAWAMOTO, Iwao
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| 著者所属 | ||||||||||
| 航空宇宙技術研究所空気力学第二部 | ||||||||||
| 著者所属（英） | ||||||||||
| en | ||||||||||
| Second Aerodynamics Division, National Aerospace Laboratory(NAL) | ||||||||||
| 出版者 | ||||||||||
| 出版者 | 航空宇宙技術研究所 | |||||||||
| 出版者（英） | ||||||||||
| 出版者 | National Aerospace Laboratory(NAL) | |||||||||
| 書誌情報 |
航空宇宙技術研究所報告 en : Technical Report of National Aerospace Laboratory TR-876 巻 876, p. 17, 発行日 1985-09 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | A new free flight testing technique has been developed in the 1m×1m blow-down supersonic wind tunnel of the National Aerospace Laboratory, and the following results were obtained through the present experimental study. (1) A new launching method in which a model is installed inside the launcher was developed, and various models were successfully launched at various angles of attack. (2) A data processing program for moving models was developed by use of a parameter identification method under the assumption of 3 degrees of longitudinal freedom of motion. Aerodynamic coefficients were successfully derived with this program. (3) Cone models, Mercury Capsule models, blunt cone capsule models, sounding rocket models and supersonic aircraft models were successfully launched. The following remarkable results were obtained from these flight tests. (3.1) Though it was very hard for the vehicles with lifting surfaces to achieve 3 degrees of longitudinal freedom of motion, there sometimes existed a short duration of this motion. The data reduction to this partial duration also showed good agreement with the conventional wind tunnel force test results in the aerodynamic coefficients. (3.2) The divergence of the pitching motion of the Mercury Capsule model was clearly shown in pictures. (4) The relations between the amount of data gathered during a run and the aerodynamic characteristics derived therefrom are discussed in this paper. (5) The excessive nonlinear terms of α for the aerodynamic expressions sometimes result in unacceptable aerodynamic characteristics. | |||||||||
| ISSN | ||||||||||
| 収録物識別子タイプ | ISSN | |||||||||
| 収録物識別子 | 0389-4010 | |||||||||
| 資料番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | 資料番号: NALTR0876000 | |||||||||
| レポート番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | レポート番号: NAL TR-876 | |||||||||
