Computation of Rarefied Gas Flows Around a NACA 0012 Airfoil

Rarefied gas flows around a NACA 0012 airfoil are simulated using both particle and continuum approaches. Three different conditions are considered: supersonic, transonic, and low subsonic. In all three cases, the continuum approach solves the Navier-Stokes equations with a slip boundary condition o...

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Bibliographic Details
Published in:AIAA journal 2001-04, Vol.39 (4), p.618-625
Main Authors: Fan, Jing, Boyd, Iain D, Cai, Chun-Pei, Hennighausen, Konstantinos, Candler, Graham V
Format: Article
Language:English
Subjects:
Aerodynamics
Applied fluid mechanics
Boundary conditions
Computer simulation
Exact sciences and technology
Flow control
Fluid dynamics
Fundamental areas of phenomenology (including applications)
Gases
Monte Carlo methods
Navier Stokes equations
Physics
Pressure
Protective coatings
Rarefied gas dynamics
Reynolds number
Slip flows
Subsonic flow
Supersonic flow
Transonic flow
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Summary:Rarefied gas flows around a NACA 0012 airfoil are simulated using both particle and continuum approaches. Three different conditions are considered: supersonic, transonic, and low subsonic. In all three cases, the continuum approach solves the Navier-Stokes equations with a slip boundary condition on the airfoil surface. For the supersonic and transonic cases, the particle method employed is the direct simulation Monte Carlo method. Because of problems with this method at the low subsonic condition, caused by excessive statistical fluctuations, a new particle method called the information preservation technique is applied. The computed density and velocity flowfields are compared with experimental data and found to be in generally good agreement. Some interesting features in the surface pressure distributions along the airfoil are found for these low-Reynolds-number flows.
ISSN:0001-1452
1533-385X
DOI:10.2514/2.1384