Aerodynamic performance enhancement by lateral blowing for reusable launch vehicles

Paper number

IAC-06-D2.5.01

Author

Dr. Kenji Tadakuma, Kyushu University, Japan

Coauthor

Prof. Shigeru Aso, Kyushu University, Japan

Coauthor

Dr. Yasuhiro Tani, Kyushu University, Japan

Year

2006

Abstract

In the past, we have reported the aerodynamic performance improvement of a wing-body configuration RLV (Reusable Launch Vehicle) using lateral blowing. However, experimental studies on the effects of other parameters in lateral blowing have not been conducted. Therefore, objective of the present study is to investigate aerodynamic effects and the mechanism due to lateral blowing on different fuselage configurations and various sweepback wings in the improvement of low-speed aerodynamic performance for RLVs and to show the effectiveness due to lateral blowing in landing process of a RLV.

   The experiments have been conducted in a transonic wind tunnel of JAXA (Japan Aerospace Exploration Agency). Lift, drag and moment are measured by a sting-type internal balance. Schlieren photography and oil flow technique have been used for flow visualization. Two fuselage-cross sections have been considered: a square and a triangular cross sections with rounded corners. And four different-sweepback wings have been considered to examine effects of the sweepback angles. Devices for the lateral blowing are installed at the bottom of the models providing a lateral jet along the trailing edge of the wing root. Direction of the blowing is perpendicular to the body axis and parallel to the trailing edge of the wing.  

   In experimental results of the square and triangular cross sections, with lateral blowing of both configurations shows the increase of lift over a wide range of angle of attack. Larger increase of lift is obtained in high angle of attack region. Especially, remarkable lift increase (maximum 1.4 times) is achieved at the "square" model. In these polar curves, lateral blowing improves the characteristics at high angle of attack. In experimental results of different sweptback wings, increase of lift due to lateral blowing in all wing types is obtained over a wide range of angle of attack. The resulting lift of flat delta wing with small sweepback and 2-dimensional wing is lager than that of the other wings in high angle of attack region. As a result of calculation for landing process, lateral blowing makes possible a shorter landing distance or a smaller landing velocity of a RLV.

   These results provided that lateral blowing has been demonstrated to be useful in producing increase of lift of RLVs with clear stall phenomenon and in shortening a landing distance or reducing a landing velocity.

Abstract document

IAC-06-D2.5.01.pdf

Manuscript document

IAC-06-D2.5.01.pdf (🔒 authorized access only).

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