Aerodynamic heating with boundary layer transition and heat protection with mass addition on blunt body in hypersonic flows

Shigeru Aso, Yuichi Kumamoto, Nobuyuki Kondo, Yoshiko Nakamura, Masayuki Katayama, Ryujiro Kurosaki

Research output: Contribution to conferencePaper

Abstract

Aerodynamic heating due to boundary layer transition and heat protection due to mass addition on blunt bodies are investigated experimentally and computationally. For the experiments on boundary layer transition a tripping wire method is used. Numerous experiments are conducted with tripping wire by changing the location by using a conventional shock tunnel. Testing conditions are at M=4.25, Po=6.0 ~ 10.1 × 105 Pa, T0=511 ~ 603 K and Reynolds number = 4.4 ~ 5.4 × 105. The results show quite remark­able increase of aerodynamic heating due to boundary layer transition. Also numerical simulations are conducted at the same experimental conditions. The results predict the sudden change of aerodynamic heating quite well. For the experiments on heat protection with mass addition a semi-sphere model is used with mass addition device at the top of the model. By changing the quantity of mass addition, heat flux distributions are measured. The results show the mass addition is quite significant in reducing aerodynamic heating at the nose of the blunt body.

Original languageEnglish
Publication statusPublished - Jan 1 1993
EventAIAA 23rd Fluid Dynamics, Plasmadynamics, and Lasers Conference, 1993 - Orlando, United States
Duration: Jul 6 1993Jul 9 1993

Other

OtherAIAA 23rd Fluid Dynamics, Plasmadynamics, and Lasers Conference, 1993
CountryUnited States
CityOrlando
Period7/6/937/9/93

All Science Journal Classification (ASJC) codes

  • Condensed Matter Physics
  • Electrical and Electronic Engineering
  • Aerospace Engineering
  • Engineering (miscellaneous)

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