Experimental study of fuselage effects on the aerodynamic performances of Reusable Launch Vehicle (RLV)

Takuro Ishida, Shigeru Aso, Yasuhiro Tani, Kenji Tadakuma, Mitsumasa Nishimura

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Experimental study to improve aerodynamic performances of RLV under the condition of constant fuselage volume has been conducted. 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. 5-types Fuselage-cross sections are tested. The models are Wing-Body configuration, and have single delta wing modified NACA0010. The experiments have been conducted in a low speed wind tunnel. In experimental result, if fuselage is stretched, maximum lift coefficient CLmax 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)max is also increased. But too long fuselage, (L/D)max is not good. In case that fuselage-cross section is changed, same results are obtained. This cause is same. Flow visualization tells that separated region and location of formation of separation vortex are related to the differences.These results provided that stretching the fuselage moderately and selecting an isosceles right triangle or half circle fuselage-cross section configurations have been improved CLmax and (L/D)max.

Original languageEnglish
Title of host publicationAIAA 57th International Astronautical Congress, IAC 2006
Pages8181-8187
Number of pages7
Publication statusPublished - Dec 1 2006
EventAIAA 57th International Astronautical Congress, IAC 2006 - Valencia, Spain
Duration: Oct 2 2006Oct 6 2006

Publication series

NameAIAA 57th International Astronautical Congress, IAC 2006
Volume12

Other

OtherAIAA 57th International Astronautical Congress, IAC 2006
CountrySpain
CityValencia
Period10/2/0610/6/06

Fingerprint

reusable launch vehicles
fuselages
Fuselages
Launch vehicles
aerodynamics
Aerodynamics
experimental study
cross section
vortex
cross sections
Vortex flow
vortices
wind tunnel
drag
triangles
visualization
effect
vehicle
Stretching
body-wing configurations

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Ishida, T., Aso, S., Tani, Y., Tadakuma, K., & Nishimura, M. (2006). Experimental study of fuselage effects on the aerodynamic performances of Reusable Launch Vehicle (RLV). In AIAA 57th International Astronautical Congress, IAC 2006 (pp. 8181-8187). (AIAA 57th International Astronautical Congress, IAC 2006; Vol. 12).

Experimental study of fuselage effects on the aerodynamic performances of Reusable Launch Vehicle (RLV). / Ishida, Takuro; Aso, Shigeru; Tani, Yasuhiro; Tadakuma, Kenji; Nishimura, Mitsumasa.

AIAA 57th International Astronautical Congress, IAC 2006. 2006. p. 8181-8187 (AIAA 57th International Astronautical Congress, IAC 2006; Vol. 12).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Ishida, T, Aso, S, Tani, Y, Tadakuma, K & Nishimura, M 2006, Experimental study of fuselage effects on the aerodynamic performances of Reusable Launch Vehicle (RLV). in AIAA 57th International Astronautical Congress, IAC 2006. AIAA 57th International Astronautical Congress, IAC 2006, vol. 12, pp. 8181-8187, AIAA 57th International Astronautical Congress, IAC 2006, Valencia, Spain, 10/2/06.
Ishida T, Aso S, Tani Y, Tadakuma K, Nishimura M. Experimental study of fuselage effects on the aerodynamic performances of Reusable Launch Vehicle (RLV). In AIAA 57th International Astronautical Congress, IAC 2006. 2006. p. 8181-8187. (AIAA 57th International Astronautical Congress, IAC 2006).
Ishida, Takuro ; Aso, Shigeru ; Tani, Yasuhiro ; Tadakuma, Kenji ; Nishimura, Mitsumasa. / Experimental study of fuselage effects on the aerodynamic performances of Reusable Launch Vehicle (RLV). AIAA 57th International Astronautical Congress, IAC 2006. 2006. pp. 8181-8187 (AIAA 57th International Astronautical Congress, IAC 2006).
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