Publication Date:
2019-07-13
Description:
A parameter-free computational procedure for transonic potential flows around an airfoil is presented. The method is based on an inexact, Newton-like iterative scheme, and a preconditioned minimal residual algorithm is used to solve the linear system of equations arising at each iterate. This iterative procedure is formulated so that the difficulties associated with the approximate factorization technique, namely the requirement of iteration parameters and the boundary conditions for the intermediate variable are eliminated. Numerical experiments are given for potential flows around NACA 0012 airfoil with different Mach numbers and different angles of attack. These results are then compared with those obtained by the approximate factorization techniques.
Keywords:
AERODYNAMICS
Type:
AIAA PAPER 83-1886
,
Computational Fluid Dynamics Conference; Jul 13, 1983 - Jul 15, 1983; Danvers, MA
Format:
text
Permalink
