Preliminary Studies on Aerodynamic Control with Direct Current Discharge at Hypersonic Speed

Yasumasa WATANABE; Yoshiki TAKAMA; Osamu IMAMURA; Tadaharu WATANUKI; Kojiro SUZUKI

doi:10.2322/tastj.8.Pe_15

e) Fluid Dynamics and Aero-thermodynamics

Preliminary Studies on Aerodynamic Control with Direct Current Discharge at Hypersonic Speed

Yasumasa WATANABE, Yoshiki TAKAMA, Osamu IMAMURA, Tadaharu WATANUKI, Kojiro SUZUKI

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Keywords: DC Plasma, Hypersonic Vehicle, Aerodynamic Control, Wind Tunnel

JOURNAL FREE ACCESS

2010 Volume 8 Issue ists27 Pages Pe_15-Pe_20

DOI https://doi.org/10.2322/tastj.8.Pe_15

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Abstract

A new idea of an aerodynamic control device for hypersonic vehicles using plasma discharges is presented. The effect of DC plasma discharge on a hypersonic flow is examined with both experiments and CFD analyses. It is revealed that the surface pressure upstream of plasma area significantly increases, which would be preferable in realizing a new aerodynamic control devices. Such pressure rise is also observed in the result of analyses of the Navier-Stokes equations with energy addition that simulates the Joule heating of a plasma discharge. It is revealed that the pressure rise due to the existence of the plasma discharge can be qualitatively explained as an effect of Joule heating.

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