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An Approximate Treatment of Laminar Heat Transfer Coefficient and its Application to the Calculation of Temperature of Super-sonic Vehicles
https://jaxa.repo.nii.ac.jp/records/34602
https://jaxa.repo.nii.ac.jp/records/34602ed047eb1-804c-4c62-b26d-5980fac14a24
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
SA2404839.pdf (869.7 kB)
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| Item type | 紀要論文 / Departmental Bulletin Paper(1) | |||||||
|---|---|---|---|---|---|---|---|---|
| 公開日 | 2015-03-26 | |||||||
| タイトル | ||||||||
| タイトル | An Approximate Treatment of Laminar Heat Transfer Coefficient and its Application to the Calculation of Temperature of Super-sonic Vehicles | |||||||
| 言語 | en | |||||||
| 言語 | ||||||||
| 言語 | eng | |||||||
| 資源タイプ | ||||||||
| 資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||||
| 資源タイプ | departmental bulletin paper | |||||||
| 著者 |
Koryo, MIURA
× Koryo, MIURA
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| 出版者 | ||||||||
| 出版者 | 東京大学航空研究所 | |||||||
| 出版者（英） | ||||||||
| 出版者 | Aeronautical Research Institute, University of Tokyo | |||||||
| 書誌情報 |
東京大學航空研究所報告 en : Report/Aeronautical Research Institute, University of Tokyo 巻 26, 号 6, p. 93-105, 発行日 1960-03 |
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| 抄録（英） | ||||||||
| 内容記述タイプ | Other | |||||||
| 内容記述 | An approximate treatment of expression for the heat transfer coefficient in compressible flow and its appliction to calculation of the skin temperature of the supersonic vehicle are presented. The paper includes the following four items. First, the weak dependence of laminar heat transfer coefficient in compressible flow upon the reference temperature at which the values of physical properties included in the Reynolds number and the thermal conductivity of the air should be taken, is shown by inspecting the total effect of those changes in physical properties with the reference temperature on the heat transfer coefficient by the use of the power law expressions for the dynamic viscosity, specific weight, and thermal conductivity of the air with temperature. Secondly, some characteristics of flight trajectory of rocket are inspected with a view of approximating them with some typical flight paterns which can easily be expressed by simple mathematical forms such as constantly accelerated (or decelerated) ascent (or descent), and these approximations are proved to be satisfactory for the purpose of calculating the temperature of the vehicle. Thirdly, with a good use of the two facts mentioned above, a simple method for calculating the skin temperature of the vehicle in super-sonic flight is proposed. Finally, the result of the flight investigation performed is presented and the measured temperature of the vehicle is compared with the calculated one obtained by the use of weak dependence of laminar heat transfer coefficient upon the reference temperature presented in the first item of the paper. | |||||||
| ISSN | ||||||||
| 収録物識別子タイプ | ISSN | |||||||
| 収録物識別子 | 0376-1061 | |||||||
| 書誌レコードID | ||||||||
| 収録物識別子タイプ | NCID | |||||||
| 収録物識別子 | AA00514444 | |||||||
| 資料番号 | ||||||||
| 内容記述タイプ | Other | |||||||
| 内容記述 | 資料番号: SA2404839000 | |||||||
