**General**

The collection of two-dimensional standard configurations, for attached flow, compiled by Bölcs and Fransson [1986] consisted of 9 different cascade- geometries, with the objective to validate both experimental data and prediction models. To this end, two different sets of data were put forward for each class of test cases. During the project it was established that most of the data selected for purely subsonic flow gave a reasonable agreement with some prediction models, which validated both the experiments and the theories. The largest computational efforts thus went into standard configurations 1 (low subsonic flow compressor cascade), 4 (cambered transonic turbine cascade), 8 (flat plate) and 9 (double circular arc profiles with low camber), with some additional work put into configurations 5 (high subsonic compressor profile) and 7 (supersonic compressor). It was concluded from the project that certain geometries and flow conditions could be accurately predicted, whereas discrepancies existed for other sample cases. Some inconsistency has been found in the definition of the pressure coefficients (steady-state and time- dependent). These are, in the present work, defined with the compressible dynamic pressure, (pw1-p1), as non-dimensionalized value. However, some researchers have used the incompressible value, (r-_v-_2/2), instead. It has been tried to, as accurately as possibly, mention these inconsistencies in the text for the various standard configurations, but it is important to keep this eventual difference in mind for some comparisons.

As the predictions on the configurations 2, 3 and 6 (see Bölcs and Fransson [1986]) were considerably smaller than on other cascade configurations, it is proposed that efforts for comparisons with low subsonic compressor blades and cambered transonic turbine blades should be reduced to configurations 1 and 4 (Figs. 3.1.1 and 3.4.1). Configuration 5 (Fig. 3.5.1) is today of larger interest than in the beginning of the project because of its systematic parameter- study from attached to stalled flow, although data are only available for one blade vibrating (here the question of superposition of influence coefficients in stalled flow may arise). Configuration 7, which treats supersonic inlet flow conditions for a compressor (Fig. 3.7.1), is also of present interest, especially as some major discrepancies between the data and the predictions exist. It is probable that some of these can be explained by viscous effects and by short comings in the numerical methods but that some can certainly also be found in the data. However, as no other complete data base has been found for supersonic flows to date, this configuration should be kept presently. Flat plate cascades, double circular arc profiles and other analytically defined geometries are still today of large interest and are necessary in order to compare prediction models with each other and to draw physical conclusions from the results. Furthermore, modern compressor blades in the high subsonic and supersonic flow domains are often derivatives of such profiles, and there seems to be a renewed interest in cascades with supersonic leading edge locus. The flat plate and double circular arc geometries (configurations 8 and 9) are thus kept in a redefined way (Figs. 3.8.1 and 3.9.1). Finally, a supplementary configuration is proposed, based on a modified NACA four digit series airfoil (Fig. 3.10.1) . It is important to note that the configurations are presently still limited to two-dimensional flow conditions, with mostly attached flow. Although numerical results today are available for solving the Navier-Stokes equations with different (steady-state) turbulence model assumptions there are hardly no separated experimental cascade data available (see however the extension of "Standard Configuration 5" below). Furthermore, three-dimensional unsteady cascade effects are today not taken into full account experimentally. However, it is reasonable to expect that some data for separated and three-dimensional flow will appear in the not too distant future. These will then, if possible, be incorporated in the present data base. All present sample cases are, furthermore, considered to be of uncoupled modes, although the coupling effects are of large importance for the stability of the blading. It is presently assumed that the coupled modes are obtained by superimposing the heaving and pitching motions. The number of aeroelastic sample cases in the report are still out of necessity large. This can not be otherwise as the standard configurations should cover all velocity domains from low subsonic to supersonic velocities and both compressor and turbine geometries, and as the interblade phase angle is a parameter of major importance in turbomachine applications. Furthermore, it is well known that the overall time-dependent blade lift and moment coefficients may give reasonable agreement between different prediction models and with experimental data, although the unsteady blade surface pressure coefficient results may represent quite different trends and to a certain extent may indicate different physical interpretations. It is thus today even more important than at the outset of the workshop to represent, for different interblade phase angles and for different cascade and flow configurations, the pressure and suction surface time-dependent pressure coefficients separately. For the benefit of those who may eventually be interested in comparing different results not included in the appendices, some publications treating results on the different standard configurations are given in each section below. Please also note that all airfoil coordinates as well as experimental data and numerical results presented, either in the first [Bölcs and Fransson, 1986] or the present standard configuration report, exist on computer files and can be obtained upon request. The plots of all the data obtained from different researchers are given in Appendix A4, and the corresponding data are listed in Appendix A3.