Shock Waves

, Volume 24, Issue 1, pp 59–67 | Cite as

Supersonic aerodynamic performance of truncated cones with repetitive laser pulse energy depositions

  • A. Sasoh
  • J.-H. Kim
  • K. Yamashita
  • T. Sakai
Original Article


We investigate the drag characteristics of truncated cones in Mach 1.94 flow with repetitive laser pulse energy depositions with a frequency of up to 80 kHz. The drag decrement is almost in proportion to the laser pulse repetition frequency, and scales with a greater-than-square power of the truncation diameter. The performance of the latter is associated with the effective area of pressure modulation and the effective residence time of vortices which are baroclinically generated after the interaction between laser-heated gas bubbles and the bow shock wave. With employing a concave head, the drag decrement is enhanced. With increasing the truncation diameter, the efficiency of energy deposition becomes higher; yet, within the operation range of this study the drag coefficient still remains high.


Laser Drag Supersonic flow  Energy deposition Baroclinic effect 

List of symbols

\(a_\infty \)

Upstream speed of sound


Drag coefficient




Baseline drag, drag without laser pulse


Base diameter of cylinder


Diameter of laser-heated gas bubble


Diameter of truncated head


Laser pulse energy incident onto test section


Laser pulse repetition frequency

\(M_\infty \)

Upstream Mach number


Stagnation pressure


Stagnation pressure without laser pulse


Radius of curvature of concaved surface



\(U_\infty \)

Upstream flow speed

\(\Delta D\)

Decrement in drag (positive when drag is reduced)

\(\Delta t\)

Time elapsed from the reference moment

\(\delta _\mathrm{i}\)

Dimensionless pulse interval, (5)

\(\eta \)

Efficiency of energy deposition

\(\rho _\mathrm{b}\)

Density of laser-heated gas bubble

\(\rho _\infty \)

Upstream density



The authors would like to thank Messrs. A. Saito, N. Shiraki and K. Kumazawa, Technical Division, Nagoya University for their valuable technical assistance. We also acknowledge valuable technical discussions with Dr. S. Yokota and Mr. A. Iwakawa. This research was supported by Japan Society for Promotion of Science as Grant-in-Aid for Scientific Research (S), No. 22226014.


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Copyright information

© Springer-Verlag Berlin Heidelberg 2013

Authors and Affiliations

  1. 1.Department of Aerospace EngineeringNagoya UniversityNagoyaJapan

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