Nonequilibrium flow computation for the space shuttle nose using unstructured meshes

Kenji Niizuma, Keisuke Sawada

Research output: Contribution to conferencePaperpeer-review


Thermochemical nonequilibrium flow computations are carried out for the purpose of reproducing surface heat transfer rate at the Space Shuttle orbiter nose-cap region during the reentry flight. For an accurate calculation of aeroheating environment at the nose-cap region, we employ a prismatic unstructured mesh system for avoiding mesh singular lines often appearing in structured meshes. Developed numerical code is first verified through comparing with the Fay and Riddell analytical formula for heat transfer rate at the stagnation point of a blunt body. Calculated results for the Space Shuttle orbiter show that the present numerical method can reproduce the flight data very well at the stagnation point, but not so well for off-stagnation points.

Original languageEnglish
Publication statusPublished - 1997 Jan 1
Event32nd Thermophysics Conference, 1997 - Atlanta, United States
Duration: 1997 Jun 231997 Jun 25


Other32nd Thermophysics Conference, 1997
Country/TerritoryUnited States

ASJC Scopus subject areas

  • Mechanical Engineering
  • Aerospace Engineering
  • Condensed Matter Physics


Dive into the research topics of 'Nonequilibrium flow computation for the space shuttle nose using unstructured meshes'. Together they form a unique fingerprint.

Cite this