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0.2m超音速風洞の圧力変動計測結果
https://jaxa.repo.nii.ac.jp/records/40305
https://jaxa.repo.nii.ac.jp/records/403052283d965-5249-416c-8492-d593c8b9aabc
名前 / ファイル | ライセンス | アクション |
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naltr0001355.pdf (927.1 kB)
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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 | 0.2m超音速風洞の圧力変動計測結果 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速風洞 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 圧力変動 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 静粛風洞 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 騒音レベル測定 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 軸流圧縮機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 集合胴 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 音圧レベル変動 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | マッハ数 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ピトー圧変動 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 流体騒音測定 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 風洞騒音測定 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic wind tunnel | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pressure fluctuation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | quiet wind tunnel | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | noise level measurement | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | axial flow compressor | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | settling chamber | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | sound pressure level fluctuation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Mach number | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Pitot pressure fluctuation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | fluid noise measurement | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | wind tunnel noise measurement | |||||
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 | Pressure fluctuation measurements in the NAL 0.2-m supersonic wind tunnel | |||||
著者 |
澤田, 秀夫
× 澤田, 秀夫× 河野, 敬× 国益, 徹也× Sawada, Hideo× Kono, Takashi× Kunimasu, Tetsuya |
|||||
著者所属 | ||||||
航空宇宙技術研究所 空力性能部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 空力性能部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 空力性能部 | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Aircraft Aerodynamics Division | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Aircraft Aerodynamics Division | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Aircraft Aerodynamics Division | ||||||
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 巻 1355, p. 1-23, 発行日 1998-08 |
|||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 0.2m超音速風洞の風路に沿った騒音レベルをマイクロフォンを用いて計測した。圧縮機から集合胴下流までの間に、音圧減衰量は約20dBに達した。この風路では集合胴までには騒音を発生させる強い音源は無いことが確かめられた。集合胴圧力変動はマイクロフォンと小型圧力変換器の2通りの方法で測定し、ほぼ同じ結果を得た。75kPaの風洞総圧に対する変動の実効値の比は、試験した総てのマッハ数で0.1%未満の値を示した。この結果、静粛風洞用に軸流圧縮機を利用することが可能であることが示された。測定部中心を通る鉛直直線上の上下0.12m間のマッハ数分布には最大0.05の変化が、また風向分布では最大1度の変化が測定された。マッハ数2.0の時の数値計算との比較から、上流部のノズル境界層が層流に維持されている可能性がある。ピトー圧変動はピトー圧の0.1%以上の変動実効値を示した。マッハ数が増加すると、この実効値も増加する。マッハ角で放射される圧力変動波の様な何らかの圧力変動を増大させる現象が、流れがノズルを通過している間に発生していることをこの増加は示している。この圧力変動を増加させる現象が存在していない場合は、パワースペクトル密度曲線は集合胴と測定部の間でその形状を維持している。このことから、測定部で圧力変動を0.1%未満に抑えるには、集合胴でも0.2%ではなく0.1%未満に抑える必要があるといえる。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The pressure fluctuations were measured along the NAL 0.2 m supersonic wind tunnel circuit with a microphone. Its attenuation is about 20 dB between the compressor and the settling chamber. There is no cause of generating noise strongly up to the settling chamber exit in this tunnel circuit. The settling chamber pressure fluctuations were measured by the two ways of a microphone and a small pressure transducer. The two results obtained are almost the same mutually. The ratio of the rms value of the fluctuations to the total pressure of 75 kPa remains under 0.1 percent at all tested Mach numbers from 1.5 to 2.5. It is possible to utilize an axial flow compressor for the quiet wind tunnel. Mach number and flow angle distributions along central 0.12 m long vertical line passing through the test section center were measured with a static pressure tube and a yaw meter. The change of largest 0.05 in Mach number and the change of largest about 1.0 degree in flow angle are observed. The comparison between the measured and numerical results at Mach number 2.0 suggests that the boundary layer on the nozzle plate maintains a laminar flow. The measured rms values of the Pitot pressure fluctuations at the test section center show the values more than 0.1 percent of the Pitot pressure. The rms value becomes larger as the Mach number increases. The increment of the rms value suggests that some phenomenon of increasing the fluctuations like the eddy Mach wave radiation has originated during the flow passing the nozzle. Because the power spectrum density curve remains its shape between the settling chamber and the test section if the phenomenon increasing the pressure fluctuation does not exist, the rms value of the pressure fluctuation at the settling chamber must be less than 0.1 percent of the total pressure unlike 0.2 percent in order to make the rms value less than 0.1 percent at the test section. | |||||
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: AA0001665000 | |||||
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-1355 |