Lateral blowing for aerodynamic performance improvement of wing-body-configuration RLV

Kenji Tadakuma, Shigeru Aso, Yasuhiro Tani

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

1 Citation (Scopus)

Abstract

An experimental study on the improvement of aerodynamic performances of wing-body-configuration RLV (Reusable Launch Vehicle) as a space transportation system by the lateral blowing in transonic and supersonic flows has been conducted. The model configuration is a wing body which has 75° /45° double delta wing of a modified NACA0010. The lateral blowing is realized by injecting a pair of sonic jets parallel to the trailing edge of the wing. The experiments have been conducted in the wind tunnel of ISAS (Institute of Space and Astronautical Science), JAXA (Japan Aerospace Exploration Agency) under the test condition of free-stream Mach number M=0.9, 1.3, 2.0, Reynolds number Re=5.06×106~6.48×106, angle of attack α= 0°~30° and jet momentum coefficient Cμ=0.0042~0.0065. The results showed that the lateral blowing increases the lift and lift-to-drag ratio. From those results, we confirmed that the lateral blowing can be useful for the improvement of aerodynamic characteristics of the wing-body-configuration RLV in transonic flow as well as in subsonic region.

Original languageEnglish
Title of host publication35th AIAA Fluid Dynamics Conference and Exhibit
Publication statusPublished - 2005
Event35th AIAA Fluid Dynamics Conference and Exhibit - Toronto, ON, Canada
Duration: Jun 6 2005Jun 9 2005

Other

Other35th AIAA Fluid Dynamics Conference and Exhibit
CountryCanada
CityToronto, ON
Period6/6/056/9/05

Fingerprint

Launch vehicles
Blow molding
Aerodynamics
Transonic flow
Supersonic flow
Angle of attack
Mach number
Wind tunnels
Drag
Momentum
Reynolds number
Experiments

All Science Journal Classification (ASJC) codes

  • Engineering (miscellaneous)
  • Aerospace Engineering

Cite this

Tadakuma, K., Aso, S., & Tani, Y. (2005). Lateral blowing for aerodynamic performance improvement of wing-body-configuration RLV. In 35th AIAA Fluid Dynamics Conference and Exhibit

Lateral blowing for aerodynamic performance improvement of wing-body-configuration RLV. / Tadakuma, Kenji; Aso, Shigeru; Tani, Yasuhiro.

35th AIAA Fluid Dynamics Conference and Exhibit. 2005.

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

Tadakuma, K, Aso, S & Tani, Y 2005, Lateral blowing for aerodynamic performance improvement of wing-body-configuration RLV. in 35th AIAA Fluid Dynamics Conference and Exhibit. 35th AIAA Fluid Dynamics Conference and Exhibit, Toronto, ON, Canada, 6/6/05.
Tadakuma K, Aso S, Tani Y. Lateral blowing for aerodynamic performance improvement of wing-body-configuration RLV. In 35th AIAA Fluid Dynamics Conference and Exhibit. 2005
Tadakuma, Kenji ; Aso, Shigeru ; Tani, Yasuhiro. / Lateral blowing for aerodynamic performance improvement of wing-body-configuration RLV. 35th AIAA Fluid Dynamics Conference and Exhibit. 2005.
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abstract = "An experimental study on the improvement of aerodynamic performances of wing-body-configuration RLV (Reusable Launch Vehicle) as a space transportation system by the lateral blowing in transonic and supersonic flows has been conducted. The model configuration is a wing body which has 75° /45° double delta wing of a modified NACA0010. The lateral blowing is realized by injecting a pair of sonic jets parallel to the trailing edge of the wing. The experiments have been conducted in the wind tunnel of ISAS (Institute of Space and Astronautical Science), JAXA (Japan Aerospace Exploration Agency) under the test condition of free-stream Mach number M∞=0.9, 1.3, 2.0, Reynolds number Re=5.06×106~6.48×106, angle of attack α= 0°~30° and jet momentum coefficient Cμ=0.0042~0.0065. The results showed that the lateral blowing increases the lift and lift-to-drag ratio. From those results, we confirmed that the lateral blowing can be useful for the improvement of aerodynamic characteristics of the wing-body-configuration RLV in transonic flow as well as in subsonic region.",
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