書誌事項
- タイトル別名
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- Numerical Study on Flow Angles and Mach Number Measurement Using the Surface Pressure of a Supersonic Aircraft with Nosecone
- ノーズコーン オ モツ チョウオンソクキ ノ ヘキメン アツリョク オ モチイタ キタイ シセイ オヨビ マッハスウ ケイソク ニ カンスル スウチ カイセキ
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抄録
Numerical simulation on the Air Data Sensor System (ADS), which measures the flow angles and Mach number using the surface pressures on a nose cone, was conducted in this study. The effect of the half cone angle on the flow angle and Mach number measurement was investigated. As a result, we found that a large half cone angle achieves a high sensitivity at the flow angle measurement. It was also found that a small half cone angle achieves a high sensitivity at the Mach number measurement. To satisfy these conflicting requests, we proposed a new shape nose cone which has two different gradients. The high sensitivity was achieved at both the flow angle measurement and Mach number measurement by this new shape nose cone.
収録刊行物
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- 日本航空宇宙学会論文集
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日本航空宇宙学会論文集 58 (676), 130-137, 2010
一般社団法人 日本航空宇宙学会
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詳細情報 詳細情報について
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- CRID
- 1390282679445856640
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- NII論文ID
- 10026612700
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- NII書誌ID
- AA11307372
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- ISSN
- 24323691
- 13446460
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- NDL書誌ID
- 10707804
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- 本文言語コード
- ja
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- データソース種別
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- JaLC
- NDL
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- CiNii Articles
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- 抄録ライセンスフラグ
- 使用不可