@inproceedings{oai:jaxa.repo.nii.ac.jp:00046357,
 author = {髙橋, 英美 and 宗像, 利彦 and 佐藤, 茂 and Takahashi, Hidemi and Munakata, Toshihiko and Sato, Shigeru},
 book = {宇宙航空研究開発機構特別資料: 第51回流体力学講演会/第37回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 51st Fluid Dynamics Conference / the 37th Aerospace Numerical Simulation Symposium},
 month = {Feb},
 note = {第51回流体力学講演会/第37回航空宇宙数値シミュレーション技術シンポジウム (2019年7月1日-3日. 早稲田大学早稲田キャンパス国際会議場), 新宿区, 東京, 51st Fluid Dynamics Conference / the 37th Aerospace Numerical Simulation Symposium (July 1-3, 2019. International Conference Center, Waseda University), Shinjuku-ku, Tokyo, Japan, The airframe-integrated linear-spike nozzle concept applied to an external nozzle for high-speed aircraft was evaluated with regard to the thrust augmentation capability in the various angles and ambient air conditions. The baseline airframe geometry was first premised to be a hypersonic waverider design. The main focus was on the vehicle aftbody. The baseline aftbody case had an external nozzle comprised of a simple divergent nozzle. The external nozzle section was hypothetically replaced with linear-spike external nozzle configurations. Performance evaluation was mainly conducted by considering the nozzle thrust generated by the pressure distribution on the external nozzle surface at the aftbody portion calculated by computer simulation at various flight conditions under angles of attack and ambient pressures. The thrust performance of the proposed linear-spike external nozzle concept was nearly equivalent to that of the baseline geometry at cruise conditions though the wall surface area can be significantly reduced. This is because the design of the proposed concept had a compression wall for the exhaust flow, which resulted in increasing the wall pressure. With this insight, the configuration with the double-ramp exhibited a potential for further improvement in thrust performance. Further potential was shown with the proposed linear-spike configuration in thrust performance under angled flight conditions as well as off-design flight conditions. Thus, benefits were obtained by employing the airframe-integrated linear-spike external nozzle concept., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1930011016, レポート番号: JAXA-SP-19-007},
 pages = {183--191},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {極超音速機外部ノズルの性能に対する飛行条件の影響評価},
 volume = {JAXA-SP-19-007},
 year = {2020}
}