Stability of Finite-Difference Equation for the Transient Response of a Flat Plate

Abstract

ment is obtained throughout the supersonic range of M = 1.0 to 4.0. Figure 2 shows the effect of varying the over-all fineness ratio for ogive-cylinder combinations at freestream Mach numbers from 1.5 to 3.0. The effect of ogive-to-cylinder length ratio is small as compared to the effect of the over-all fineness ratio, which affects average skin friction greatly below an over-all fineness ratio of approximately 7. Figure 3 compares the effects of various body shapes on local skin-friction coefficient, for a typical freestream Mach number of 2.0. The ogive cylinder, cone, and parabolic body of revolution show somewhat the same general skin-friction distribution along their forebodies where pressure gradients are favorable (dp/dx < 0). The effects of the adverse pressure gradients on the local skin-friction distribution are most pronounced on the parabolic body of revolution which has a rapidly increasing pressure near the aft end. This creates a rapidly falling skin-friction coefficient that approaches the point of separation. The calculation procedure appears to be capable of estimating the separation point, in the case of adverse pressure gradient, although no attempt to verify its accuracy is made.