Unified calculation of hypersonic flowfieid for a reentry vehicle

Toshiyuki Suzuki; Michiko Furudate; Keisuke Sawada

Unified calculation of hypersonic flowfieid for a reentry vehicle

Toshiyuki Suzuki, Michiko Furudate, Keisuke Sawada

ENG - Aerospace Engineering

Research output: Contribution to conference › Paper › peer-review

Abstract

A unified CFD method is developed that integrates numerical methods for solving specific problems related to aerodynamic heating phenomena and ablative heatshield. Using this unified CFD code, trajectory-based analysis on the aerodynamic heating environment for the MUSES-C super-orbital reentry capsule is conducted. Converged solutions can be obtained by loosely coupling CFD code and CMA code within a few iterations. The results show that the wall surface temperature in the downstream region is significantly elevated by the effect of turbulence due to ablation product gas. Wall temperature as well as the recession rate at the stagnation point along the entry trajectory is found to duplicate well with the existing predictions.

Original language	English
Publication status	Published - 2001 Dec 1
Event	39th Aerospace Sciences Meeting and Exhibit 2001 - Reno, NV, United States Duration: 2001 Jan 8 → 2001 Jan 11

Other

Other	39th Aerospace Sciences Meeting and Exhibit 2001
Country/Territory	United States
City	Reno, NV
Period	01/1/8 → 01/1/11

ASJC Scopus subject areas

Space and Planetary Science
Aerospace Engineering

Cite this

@conference{992a8f5fa0504fe58c68bc8f878ce96f,

title = "Unified calculation of hypersonic flowfieid for a reentry vehicle",

abstract = "A unified CFD method is developed that integrates numerical methods for solving specific problems related to aerodynamic heating phenomena and ablative heatshield. Using this unified CFD code, trajectory-based analysis on the aerodynamic heating environment for the MUSES-C super-orbital reentry capsule is conducted. Converged solutions can be obtained by loosely coupling CFD code and CMA code within a few iterations. The results show that the wall surface temperature in the downstream region is significantly elevated by the effect of turbulence due to ablation product gas. Wall temperature as well as the recession rate at the stagnation point along the entry trajectory is found to duplicate well with the existing predictions.",

author = "Toshiyuki Suzuki and Michiko Furudate and Keisuke Sawada",

year = "2001",

month = dec,

day = "1",

language = "English",

note = "39th Aerospace Sciences Meeting and Exhibit 2001 ; Conference date: 08-01-2001 Through 11-01-2001",

}

TY - CONF

T1 - Unified calculation of hypersonic flowfieid for a reentry vehicle

AU - Suzuki, Toshiyuki

AU - Furudate, Michiko

AU - Sawada, Keisuke

PY - 2001/12/1

Y1 - 2001/12/1

N2 - A unified CFD method is developed that integrates numerical methods for solving specific problems related to aerodynamic heating phenomena and ablative heatshield. Using this unified CFD code, trajectory-based analysis on the aerodynamic heating environment for the MUSES-C super-orbital reentry capsule is conducted. Converged solutions can be obtained by loosely coupling CFD code and CMA code within a few iterations. The results show that the wall surface temperature in the downstream region is significantly elevated by the effect of turbulence due to ablation product gas. Wall temperature as well as the recession rate at the stagnation point along the entry trajectory is found to duplicate well with the existing predictions.

AB - A unified CFD method is developed that integrates numerical methods for solving specific problems related to aerodynamic heating phenomena and ablative heatshield. Using this unified CFD code, trajectory-based analysis on the aerodynamic heating environment for the MUSES-C super-orbital reentry capsule is conducted. Converged solutions can be obtained by loosely coupling CFD code and CMA code within a few iterations. The results show that the wall surface temperature in the downstream region is significantly elevated by the effect of turbulence due to ablation product gas. Wall temperature as well as the recession rate at the stagnation point along the entry trajectory is found to duplicate well with the existing predictions.

UR - http://www.scopus.com/inward/record.url?scp=84897867316&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84897867316&partnerID=8YFLogxK

M3 - Paper

AN - SCOPUS:84897867316

T2 - 39th Aerospace Sciences Meeting and Exhibit 2001

Y2 - 8 January 2001 through 11 January 2001

ER -

Unified calculation of hypersonic flowfieid for a reentry vehicle

Abstract

Other

ASJC Scopus subject areas

Other files and links

Fingerprint

Cite this