Abstract
As interest in hypersonic flight is once again growing, this is an opportune time to re-examine the applicability and limitations of our gas dynamic models. It is particularly important to address the flow regime between non-continuum and continuum gas dynamics (the slip or transitional regime) because these flows may be common on future hypersonic vehicles and they are very poorly understood. This paper uses a full NavierStokes method and a molecular simulation method to analyze an indented nose cone at hypersonic Mach numbers. The Navier-Stokes code is based upon a finite-volume, explicit Runge-Kutta time-marching scheme. The molecular simulation method is based on the Direct Simulation Monte Carlo (DSMC) method. Theoretical and numerical differences between the two methods are discussed. Heat transfer predictions are compared to experimental data.
| Original language | English (US) |
|---|---|
| State | Published - Jan 1 1998 |
| Event | AIAA 23rd Thermophysics, Plasmadynamics and Lasers Conference, 1988 - San Antonio, United States Duration: Jun 27 1988 → Jul 29 1988 |
Other
| Other | AIAA 23rd Thermophysics, Plasmadynamics and Lasers Conference, 1988 |
|---|---|
| Country | United States |
| City | San Antonio |
| Period | 6/27/88 → 7/29/88 |
Fingerprint
All Science Journal Classification (ASJC) codes
- Mechanical Engineering
- Aerospace Engineering
- Engineering(all)
Cite this
}
A comparison of navier-stokes and monte carlo methods for hypersonic flows. / Long, Lyle Norman.
1998. Paper presented at AIAA 23rd Thermophysics, Plasmadynamics and Lasers Conference, 1988, San Antonio, United States.Research output: Contribution to conference › Paper
TY - CONF
T1 - A comparison of navier-stokes and monte carlo methods for hypersonic flows
AU - Long, Lyle Norman
PY - 1998/1/1
Y1 - 1998/1/1
N2 - As interest in hypersonic flight is once again growing, this is an opportune time to re-examine the applicability and limitations of our gas dynamic models. It is particularly important to address the flow regime between non-continuum and continuum gas dynamics (the slip or transitional regime) because these flows may be common on future hypersonic vehicles and they are very poorly understood. This paper uses a full NavierStokes method and a molecular simulation method to analyze an indented nose cone at hypersonic Mach numbers. The Navier-Stokes code is based upon a finite-volume, explicit Runge-Kutta time-marching scheme. The molecular simulation method is based on the Direct Simulation Monte Carlo (DSMC) method. Theoretical and numerical differences between the two methods are discussed. Heat transfer predictions are compared to experimental data.
AB - As interest in hypersonic flight is once again growing, this is an opportune time to re-examine the applicability and limitations of our gas dynamic models. It is particularly important to address the flow regime between non-continuum and continuum gas dynamics (the slip or transitional regime) because these flows may be common on future hypersonic vehicles and they are very poorly understood. This paper uses a full NavierStokes method and a molecular simulation method to analyze an indented nose cone at hypersonic Mach numbers. The Navier-Stokes code is based upon a finite-volume, explicit Runge-Kutta time-marching scheme. The molecular simulation method is based on the Direct Simulation Monte Carlo (DSMC) method. Theoretical and numerical differences between the two methods are discussed. Heat transfer predictions are compared to experimental data.
UR - http://www.scopus.com/inward/record.url?scp=84999273703&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=84999273703&partnerID=8YFLogxK
M3 - Paper
AN - SCOPUS:84999273703
ER -