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Pstd), along with pitch and yaw angles and Euler-based tem- peratures (normalized by the reference temperature tstd), are provided in tables V and VI for the design and off-design con- ditions, respectively. These tables provide the necessary inlet boundary conditions for computational analyses of the LSCC flow field. Laser Anemometer Measurements Several features of the velocity measurements should be kept in mind when the laser anemometer data are being inter- preted. First, the average of all the velocity measurements in a given window was often considered as a single velocity mea- surement at a point located in the center of the measurement window. It is important to remember that these measurements did not actually occur at a single point, but rather in a region centered about the plotted point. Second, although each indi- vidual velocity measurement was an instantaneous measure- ment of the unsteady velocity field, the measurements acquired in each measurement window were acquired over thousands of separate rotor revolutions. The average of all velocity measure- ments acquired in a given window was, therefore, the ensemble-averaged velocity at the window location (with the averaging period being one rotor revolution). Furthermore, the ensemble-averaged laser anemometer measurements for the In this report aerodynamic performance data are presented for two operating conditions at 1862 rpm: at the design mass flow rate and at a lower flow rate. The location of these two points on the rotor operating line are shown in figure 17 along with additional aerodynamic performance measurements not reported in detail herein. The data shown in figure 17 are based on plenum total pressure, bellmouth mass flow, and aerody- namic survey measurements acquired at survey station 2 down- stream of the rotor. The aerodynamic survey results obtained at station 2 for the design and off-design conditions are presented in tables VII and VIII, respectively. The overall rotor aerody- namic performance based on the energy-averaged total pres- sure ratio and the mass-averaged total temperature ratio at same relative window location in each blade passage were station 2, as well as the temperature- and torque-based mance, is shown at the bottom of each table. Surface Static Pressure Measurements perfor- averaged for all blade passages to produce a blade-to-blade dis- tribution of passage-averaged velocities in each blade passage. Last, the three-dimensional velocity measurements were a re- sult of combining measurements acquired independently for two separate orientations of the laser beam optical axis; there- fore these measurements were not acquired concurrently, al- though they were acquired during the same run session. Figures 24 to 46 and 47 to 51 are, respectively, plots of the pitchwise distributions of laser anemometer measurements, at design and off-design conditions, for selected stations through the impeller. Typically these data are plotted at 5-percent-of- span increments at a resolution of 200 points per pitch, pro- ceeding from suction to pressure surface. For results acquired within the impeller, the blade is indicated by the cross-hatched region to the right of each plot. Figures 52 to 74 and 75 to 79 are contour plots of laser- anemometer-measured throughflow velocity distributions for all stations through the impeller at design and off-design con- ditions, respectively. Likewise, figures 80 to 102 and 103 to 107 are wire-frame plots of laser-anemometer-measured throughflow velocity dis- tributions for all stations through the impeller at design and off-design conditions. These data are typically plotted at 5-percent-of-span increments at a resolution of 200 points per pitch. Figures 108 to 130 and 131 to 135 are vector plots of laser- anemometer-measured secondary velocity distributions at design and off-design conditions, respectively. Data are plotted at 5-percent-of-span increments for all stations through the impeller. The page numbers of figures 24 to 135 are given in table XIII. Data Uncertainty and Reproducibility Aerodynamic probe measurements.--The uncertainty of the aerodynamic probe measurements is indicated in table XIV. The rotor blade surface static pressures measured at design and off-design conditions are provided in tables IX and X, re- spectively, and they are plotted in figures 18 and 19 as a func- tion of percent of meridional distance for each spanwise loca- tion. The static pressures shown in these tables and figures have been normalized by the reference pressure Pstd- Fig- ures 20 and 21 show contour plots of the blade surface static pressures normalized by Pstd for design and off-design condi- tions, respectively. The locations of the static pressure taps (see table VIII) are indicated on the contour plots to aid in interpre- tation of the contours. The shroud surface static pressures measured over a range of mass flows were normalized by the reference pressure Pstd and are given in table XI. Figure 22 is a contour plot of these data. The locations where the shroud static pressures were measured are provided in table IV. Flow Visualization Figure 23 shows the ammonia-Ozalid blades' pressure and suction surfaces at the design flow condi- tion. The traces are arrows depicting the direction of flow. They were computer-generated from measurements of the ori- entation of the actual flow traces acquired in the experiment. Also noted in figure 23 are the laser anemometer survey stations and corresponding spanwise measurement locations nearest to the ammonia-Ozalid flow traces. The measured pitch angles of the ammonia-Ozalid flow traces are provided in table XII, and the method for determining them is described in the Flow Visualization subsection of the Test Procedure section. 10 flow traces on thePDF Image | Laser anemometer measurements of the three-dimensional rotor flow
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