**Eighth standard configuration (flat plate cascades
at different flow conditions)**

As flat plate configurations are the most important to compare against as regards to the numerical completeness and accuracy of non-analytical prediction models, it is important that such configurations cover as wide a scope as possible, especially as regards to Mach number variations. The number of aeroelastic sample cases will thus forcibly be large, but this is not a major problem as the analytical flat plate solutions used as baseline comparisons are usually fairly fast, and researchers who may want to compare a numerical result against an analysis will only choose the domain of current interest and perform a few calculations. The 35 original aeroelastic sample cases will be kept (Fig. 3.8.1 and Table 3.8.1). The time-dependent cases 36 to 42, corresponding to some of the earlier cases but with a reduced frequency of k=0.5 instead of k=1.0, have been added. This lower reduced frequency (k=0.5) was recommended as the higher reduced frequency showed some differences, which may eventually be attributed to some numerical effects, between the different prediction models. To these aeroelastic test cases are added two supplementary steady-state conditions (Figs. 3.8.2). These, denoted as aeroelastic test cases 43-54 and suggested by Dr. Verdon, are the well known "Cascades A and B" as defined by Verdon [1973] and Verdon and McCune [1975]. These cascade configurations were originally carefully selected to highlight wave reflections in supersonic flow and have been used frequently in the past as comparison for a number of analyses. They have provided useful insight into the physical phenomena of unsteady supersonic flow on vibrating flat plates and interesting, often positive, results from the comparisons. It is believed that they also in the future should be of special interest as baseline comparisons for numerical models for supersonic flow, also for supersonic leading edge locus configurations. As far as the present authors are aware, all pressure coefficient results have been presented with the incompressible dynamic pressure, (r-_•v-_2/2), as non-dimensionalized value.