Experimental study of fuselage effects on the aerodynamic performances of reusable launch vehicle (rlv)

Paper number

IAC-06-D2.P.1.03

Author

Mr. Takuro Ishida, Kyushu University, Japan

Coauthor

Prof. Shigeru Aso, Kyushu University, Japan

Coauthor

Dr. Yasuhiro Tani, Kyushu University, Japan

Coauthor

Dr. Kenji Tadakuma, Kyushu University, Japan

Coauthor

Mr. Mitsumasa Nishimura, Kyushu University, Japan

Year

2006

Abstract

By now, the study about fuselage-cross sections for Reusable Launch Vehicle (RLV) have been conducted to improve aerodynamic performances. In that study, two fuselage-cross sections were considered: an isosceles right triangle and a square with rounded corners. And compared aerodynamic performances of the two models subjected to conform to full length and projected area. So I find the problem that the fuselage volumes are not same. Therefore, objective of this study is to improve aerodynamic performances of RLV under the condition of constant fuselage volume.

Two means have been considered to maintain constant volume. One is stretching the fuselage and remaining fuselage-cross section configuration. Fuselage-cross section is an isosceles right triangle. The other is changing the fuselage-cross section configurations and remaining full length. Fuselage-cross sections are an isosceles right triangle, an equilateral triangle, a rectangle, a circle, and a half circle. The models are Wing-Body configuration, and have single delta wing modified NACA0010 rear part of fuselage. The experiments have been conducted in a low speed wind tunnel. Lift, drag and moment are measured by a balance. Smoke-wire technique have been used for flow visualization. And also, to get more correct aerodynamic data, free flight tests using Remotely Piloted Vehicle (RPV) have been conducted.

In experimental result, if fuselage is stretched, maximum lift coefficient and wing- stalled angle of attack are increased. This is related fuselage separation vortex. As fuselage is stretched, effected region by this vortex is expanded. So, vortex is more developed. Maximum lift-to-drag ratio (L/D) is also increased. But too long fuselage, maximum L/D is not good. As for maximum L/D, proper fuselage length is existed. In case that fuselage-cross section is changed, lift coefficient, wing- stalled angle of attack and maximum L/D are also changed. This cause is same; fuselage separation vortex. Flow visualization using smoke-wire technique tells that separated region and location of formation of separation vortex are related to the differences.

These result provided that stretching the fuselage moderately and selecting an isosceles right triangle or half circle fuselage-cross section configurations have been improved maximum lift coefficient and maximum L/D.

Abstract document

IAC-06-D2.P.1.03.pdf

Manuscript document

IAC-06-D2.P.1.03.pdf (🔒 authorized access only).

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