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航空研究所長距離機性能計算書
https://jaxa.repo.nii.ac.jp/records/35412
https://jaxa.repo.nii.ac.jp/records/35412faad3c60-d670-46c9-984d-5422faefdf7e
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
SA4146947.pdf (3.7 MB)
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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 | 航空研究所長距離機性能計算書 | |||||||||
| 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_6501 | |||||||||
| 資源タイプ | departmental bulletin paper | |||||||||
| その他のタイトル（英） | ||||||||||
| その他のタイトル | Performance Calculations on the Koken Long-Range Monoplane. | |||||||||
| 著者 |
木村, 秀政
× 木村, 秀政
× KIMURA, Hidemasa
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| 出版者 | ||||||||||
| 出版者 | 東京帝國大學航空研究所 | |||||||||
| 出版者（英） | ||||||||||
| 出版者 | Aeronautical Research Institute, Tokyo Imperial University | |||||||||
| 書誌情報 |
東京帝國大學航空研究所報告 en : Report of Aeronautical Research Institute, Tokyo Imperial University 巻 13, 号 166, p. 299-385, 発行日 1938-08 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | The performance of the Koken Long-Range Monoplane, when fitted with the "SW-1" wooden propeller, was calculated over the range of total weight from 5,000kg. to 9,500kg. This monoplane set up the world's distance record of 11,651.011km. over a closed circuit, and at the same time the international speed record of 186.197km/h over 10,000km. in May, 1938. As the aerodynamic characteristics of the aeroplane, the results of wind tunnel tests carried out systematically at the Institute were used. The maximum c_z/c_x of the complete aeroplane with undercarriage retracted is 18.9 as shown in Fig.4, p.313. The characteristics of the propeller, tested on the model with fuselage, are shown in Fig.10, p.322. The propeller, with a diameter of 4.00m, has a propulsive efficiency of 79 per cent at cruising speed, and a static thrust of 1686kg. absorbing 784 FP. at 1,700 r. p. m. The engine, "Kawasaki Special" liquid-cooled twelve-cylinder in V, develops 800 FP. at 1,800 r. p. m. at sea level. The results of bench test carried out at the Institute show that the fuel consumption rate at cruising condition varies from 184g/FP/h to 203g/FP/h according to weight and speed. The principal characteristics and the calculated performance of the monoplane are as follows: Number of crew 2 or 3 Span 27.93m. Length overall 15.06m. Height overall 3.84m. Wing area 87.3m^2. Empty weight with fixed equipment 4225kg. Loaded weight 9200～9500kg. Total capacity of fuel tanks 75001. Performance: Total weight (kg) 5000 9500 Wing loading (kg/m^2) 57.3 108.8 Power loading (kg/FP) 6.25 11.9 Wing power (FP/m^2) 9.16 9.16 Maximum speed at sea level (km/h) 250 243 Cruising speed at 2000m at 75% power (km/h) 247 233 Economical speed at 2000m (km/h) 155 208 Stalling speed (km/h) 96 132 Initial rate of climb (m/s) 6.06 2.10 Climb to 2000m (min-sec) 6-31 23-55 Service ceiling (m) 7310 2900 Kilometres per kilogram of fuel at 2000m (km) 386 2.26 Range at 2000m (km) - 13550 Duration at 2000m (h) - 75 Take-off run on concrete runway (m) 250 1250 The results of flight tests indicated that they agreed fairly well with those of the calculations here described, but the comparisons between them will be discussed in the later. | |||||||||
| 書誌レコードID | ||||||||||
| 収録物識別子タイプ | NCID | |||||||||
| 収録物識別子 | AA00387631 | |||||||||
| 資料番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | 資料番号: SA4146947000 | |||||||||
