Abstract
Abstract To study the influence of initial fields on computation results, the author, starting from a two-dimensional steady transonic small-disturbance equation, has computed the shock wave strengths and lift coefficients for the NACA0012 airfoil by the mixed finite difference relaxation iteration method. The computed results show that if (1) incident flows are supercritical, (2) a nonconservative difference scheme is used to capture shock waves, and (3) the computations are iterated with the initial fields at the lower entropy values (zero values or computed results of flow fields with smaller angles of attack or Mach numbers), then correct converged solutions can be obtained. Otherwise, erroneous converged solutions might be obtained. If incident flows are subcritical and shock waves do not appear in the flow field, then the computed results do not depend on the choice of the initial fields. This means that the converged solution is unique.
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