JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
64576000.pdf2.8 MB
title静粛超音速研究機基本設計低ブーム確認超音速風洞試験
Other TitlePreliminary Supersonic Wind Tunnel Test for Low Sonic-boom Design Validation of Silent Supersonic Technology Demonstrator
Author(jpn)牧野, 好和; 野口, 正芳
Author(eng)Makino, Yoshikazu; Noguchi, Masayoshi
Author Affiliation(jpn)宇宙航空研究開発機構航空プログラムグループ超音速機チーム; 宇宙航空研究開発機構航空プログラムグループ超音速機チーム
Author Affiliation(eng)Supersonic Transport Team, Aviation Program Group, Japan Aerospace Exploration Agency (JAXA); Supersonic Transport Team, Aviation Program Group, Japan Aerospace Exploration Agency (JAXA)
Issue Date2010-01-29
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication titleJAXA research and development memorandum
宇宙航空研究開発機構研究開発資料
VolumeJAXA-RM-09-006
Publication date2010-01-29
Languagejpn
eng
AbstractNear-field pressure signatures of the silent supersonic technology demonstrator are measured in the JAXA 1 m x 1 m supersonic wind tunnel in its preliminary design phase for validating its low sonic-boom design. The low sonic-boom features are observed in the measured pressure signatures which are compared to those predicted by some CFD codes. Some flight requirements which are imposed on the demonstrator such as the retention of flight Mach number, variations in the pitch or roll angle, are validated by the comparison of near-field pressure signatures for these effects.
低ソニックブーム設計技術の実証を第一の目的とする静粛超音速研究機の基本設計において,低ブーム設計検証のためにJAXA1m×1m超音速風洞において機体近傍場の圧力分布計測を実施した.計測された圧力波形は設計時の数値解析結果と同様に,低ブーム特性を示していることが確認された.また,マッハ数や迎角,ロール角等の飛行条件がブーム特性に与える影響について調べ,研究機に求められる飛行制御要求の妥当性についても検証した.
DescriptionOriginal contains color illustrations
形態: カラー図版あり
Keywordssupersonic transport, sonic-boom, wind tunnel
Document TypeTechnical Report
JAXA Category研究開発資料
ISSN1349-1121
NCIDAA11983593
SHI-NOAA0064576000
Report NoJAXA-RM-09-006
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/20724


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