Improvement of Aerodynamic Performances for Reusable Launch Vehicles Using the Lateral Blowing
- Paper number
IAC-05-D2.5.03
- Author
Dr. Kenji Tadakuma, Kyushu University, Japan
- Coauthor
Prof. Shigeru Aso, Kyushu University, Japan
- Coauthor
Dr. Yasuhiro Tani, Kyushu University, Japan
- Coauthor
Mr. Kentaro Hayashi, Mistubishi Space Software Co. Ltd., Japan
- Year
2005
- Abstract
The object of this study is to investigate the effect and the mechanism of the aerodynamic performance improvement by the lateral blowing for wing-body configuration of RLVs (Reusable Launch Vehicles). In this paper, the experimental results were reported to reveal the effect and the mechanism on improvement of aerodynamic performances using the lateral blowing in transonic and supersonic flow.
The experiments have been conducted in the wind tunnel of ISAS, JAXA. The model has 75 ∘/45 ∘ double delta wings of the modified NACA0010. The lateral blowing is a pair of small sonic jets from the trailing edge of the wing root.The blowing direction is perpendicular to a body axis and parallel to the trailing edge. A sting-type internal balance measures lift, drag and moment under the test condition of angle of attack 0 ∘ <α<30 ∘, Mach number M ∞= 0.9, 1.3, 2.0, Reynolds number Re=5.06×10 6∼6.48×10 6, and jet momentum coefficient Cµ=0.0042∼0.0065. Schlieren photography and oil flow technique have been used for flow visualization.
The lateral blowing shows the increase of the lift all over the angle of attack and the constant increment. Such lift increases are about 0.03 larger than that of the “No Blowing”. The lift-to-drag ratio is enhanced in low angle of attack region compared to that of the “Wing body only”. Maximum increase of the lift-to-drag ratio is about 1.4 times as large as that of the “No Blowing”. The lift-to-drag ratio in subsonic flow region is greater than that of over M ∞= 1.3. The improvement by the lateral blowing is smaller as Mach number is increased. From oil flow visualization results, the mechanism of the lift increase by the lateral blowing are summarized as follows: (a) Upper surface flow accelerated near the trailing edge due to the jet results in the increase of the negative pressure. (b) The breakdown of the leading-edge separation vortex is delayed. (c) The pressure near the trailing edge on the lower surface is increased because the jet stream works as an obstacle lying laterally normal to the main flow.
The lateral blowing has been demonstrated to be useful for improvement of aerodynamic performances of a wing-body-configuration of RLVs in transonic and supersonic flow region.
- Abstract document
- Manuscript document
IAC-05-D2.5.03.pdf (🔒 authorized access only).
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