Skip Navigation


Skip Side Navigation

Assistant Professor Hiroshi Ozawa


  • Ph.D., Aerospace Engineering- 2010 Nagoya University


  • Unsteady Aerothermodynamics
  • Temperature/Pressure Sensitive Paints 
  • Hypersonic Boundary-Layer Transition
  • Transient High-Speed Wind Tunnel Experiments
  • Optical Flow Diagnostics for Transient High-Speed Flows
  • Shock-Shock/Shock-Boundary-Layer Interactions


  • Associate Professor in the Department of Aeronautics and Astronautics, Tokyo Metropolitan University (04.2019-08.2021)
  • Assistant Professor in the Department of Aerospace Engineering, Tokyo Metropolitan University (04.2013-03.2019)
  • Postdoctoral Researcher in Spacecraft Department, DLR (04.2010-03.2013)
  • 21-Century COE Program “Frontiers Computational Science” in Nagoya University, Research Assistant, 2007-2010.
  • Honda Motor Company, Limited, R&D Center, Aerodynamics division. (04.2006-11.2006, full-time employee)

Tokyo Metropolitan University undergraduate courses:

  • Seminar for Freshman
  • Introduction to Aerospace Engineering I (Omnibus)
  • Introduction to Aerospace Engineering II (Omnibus)
  • Aerospace propulsion I
  • Aerodynamics II
  • Aerodynamics Experiments I (Omnibus)
  • Aerodynamics Experiments II (Omnibus)

Graduate courses:

  • High-speed aerothermodynamics
  • Exercise of Project Management


Distinguished Young Researcher Award in Fluid Mechanics, “Experimental investigation of high-speed aerothermodynamics phenomena using Temperature Sensitive Paint”, the Japan Society of Fluid Mechanics, 2019.

DLR-DAAD Research Fellowship, 2010.

21-Century COE Program, FSC Competition at Nagoya University, Excellent Award, 2008. 


1.   Fluid dynamics Handbook, 3rd edition, University of Tokyo press. (joint author, to be published)

2.  Whalen TJ, Laurence SJ, Marineau E, Ozawa H (2021) "A Green's function approach to heat-flux estimation from temperature-sensitive paint measurements", Measurement Science and Technology (Special Issue on Pressure-Sensitive and Temperature-Sensitive Paints for Measuring High Speed and Unsteady Flows), 32:114011.

3.  Laurence SJ, Ozawa H, Schramm JM, Hannemann K (2021) "Combined combustion and heat-flux measurements on a supersonic jet-in-crossflow configuration using luminescent paint", Experiments in Fluids, 62:154.

4.  Ozawa H (2020), “Application of Temperature-Sensitive Paint on a Hypersonic Vehicle and in a Shock-tube”, J of TSJ., ‘Turbomachinery’, Turbomachinery Society of Japan, 48(1), pp.36-42.

5.  Ozawa H (2019) Experimental investigation of high-speed aerothermodynamics phenomena using Temperature Sensitive Paint”, the Japan Society of Fluid Mechanics, NAGARE, vol. 38, pp.156-161.

6.  Laurence SJ, Ozawa H, Schramm JM, Hannemann K (2019) Heat-flux measurements on a Hypersonic intake ramp using fast-response temperature sensitive paint, Exp. Fluids., 60(4):70

7.  Ozawa H, Laurence SJ (2018) Experimental Investigation of the Shock-Induced Flow over a Wall-Mounted Cylinder, J. Fluid. Mech., Vol.849, pp.1009-1042.

8.  Nagai H, Mitsuo K, Nakakita K, Sugioka Y, Ozawa H and Yorita D (2018) PSP and TSP Application in Aerospace Fields, The Visualization Society of Japan, Vol. 38, No. 148.

9.  Ozawa H (2016) Experimental Study of Unsteady Aerothermodynamic Phenomena on Shock-Tube Wall using Fast-response Temperature-sensitive-Paints, Phys. Fluids, 28(4): 046103.

10.    Ozawa H, Laurence SJ, Schramm JM, Wagner A, Hannemann K (2015) Fast-response temperature-sensitive-paint measurements on a hypersonic transition cone, Exp. Fluids., 56(1):1853.


  • The Japan Society for Aeronautical and Space Sciences (JSASS)
  • The Japan Society of Fluid Mechanics
  • Investigation and Control of Transition to Turbulence
  • Molecular Imaging Technology
  • American Institute of Aeronautics and Astronautics (AIAA)
  • International Workshop on Shock Tube Technology (IWSTT)

Contact Info

(405) 325-3176
Felgar Hall 236

Lab website