書誌事項
- タイトル別名
-
- Wind Tunnel Testing and Numerical Analysis on Angle-of-Attack 60º Side-Force Characteristics of Double-Cone Reusable Rocket
抄録
<p>In order to reduce launch cost, ISAS/JAXA has been developing a reusable vertical-takeoff and vertical-landing (VTVL) rocket. Currently, the prototype model ``RV-X'' is being developed. This rocket adopts nose-entry returning flight system and needs the turnover maneuver before landing. It is known that the side-force is generated by asymmetrical vortices when the rocket flies at high angles of attack, and also known that the apex angle of the nose cone affects the magnitude of side force. In this study, we conducted wind tunnel testing and CFD on the aerodynamics of the RV-X with a double-cone nose. The surface flow field were used for CFD validation. Consequently, we obtained following findings: 1) the slight asymmetry of the experimental model due to machining accuracy and surface roughness significantly affected the magnitude of side force, 2) the flow field by CFD at 60º angle-of-attack was qualitatively consistent with the surface flow field visualized by an oil-flow technique, 3) the vortices generated from the nose collapsed at the rear part of the body and formed an asymmetrical flow field, 4) the generation of asymmetrical vortices with respect to the angle of attack was influenced primarily by the first cone, but the created side force was determined by interactions of the first and the second cones. </p>
収録刊行物
-
- 日本航空宇宙学会論文集
-
日本航空宇宙学会論文集 70 (1), 14-21, 2022
一般社団法人 日本航空宇宙学会
- Tweet
詳細情報 詳細情報について
-
- CRID
- 1390009562055925888
-
- NII論文ID
- 130008158036
-
- ISSN
- 24323691
- 13446460
-
- 本文言語コード
- ja
-
- データソース種別
-
- JaLC
- Crossref
- CiNii Articles
-
- 抄録ライセンスフラグ
- 使用不可