A study on aerodynamic heating reduction due to opposing jet in hypersonic flow

Shigeru Aso, K. Hayashi, M. Mizoguchi

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

14 Citations (Scopus)

Abstract

In the present study, aerodynamic heating reduction due to opposing jet from the top of blunt body is experimentally and numerically investigated. Experiments are conducted by using a conventional blowdown type wind tunnel. In the experiments, a hemisphere model is installed into supersonic free stream of Mach number of 4 and the coolant N2 gas is injected through a nozzle. Significant decreases of surface heat flux are obtained and opposing jet is proved to be effective on aerodynamic heating reduction at the nose of the blunt body. Numerical analysis is conducted in order to understand more detailed flow field. In numerical analysis, axisymmetric full Navier-Stokes equations are solved by an implicit finite difference method. LU-ADI and AUSM-DV scheme are used. Numerical results show good agreements with experiments and more detailed investigation of the flow indicates that the most effective aerodynamic heating reduction is occurred in the recirculation region.

Original languageEnglish
Title of host publication40th AIAA Aerospace Sciences Meeting and Exhibit
Publication statusPublished - 2002
Event40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States
Duration: Jan 14 2002Jan 17 2002

Other

Other40th AIAA Aerospace Sciences Meeting and Exhibit 2002
CountryUnited States
CityReno, NV
Period1/14/021/17/02

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

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