This report describes a FORTRAN computer program developed to create a contour plot of experimentally determined static pressure distributions existing over the blade tips of a transonic compressor rotor. The input data used by the program was the digitized, ensemble averaged output of casing mounted high frequency response pressure transducers. The resulting plots give the compressor designer important information regarding shock position and strength and wave pattern.
The results of an experimental evaluation of one compressor test of a series of design parameter investigations are presented. The purpose of the parametric blade design study was to investigate the effects of specific rotor blade design parameters on the performance of one compressor configuration of current interest with state-of-the-art performance. It was the intent of the program to vary only one design parameter at a time, keeping the other ...
The results of an experimental evaluation of one compressor test of a series of design parameter investigations are presented. The purpose of the parametric blade design study was to investigate the effects of specific rotor blade design parameters on the performance of one compressor configuration of current interest with state-of-the-art performance. It was the intent of the program to vary only one design parameter at a time, keeping the other ...
The results of an experimental evaluation of one compressor test of a series of design parameter investigations are presented. The purpose of the parametric blade design study was to investigate the effects of specific rotor blade design parameters on the performance of one compressor configuration of current interest with state-of-the-art performance. It was the intent of the program to vary only one design parameter at a time, keeping the other ...
A new subroutine and several modified subroutines of program UD0300 are presented along with a discussion of the three-dimensional shock model used in their development. The basis for the model is found in a paper by D. Prince in Journal of Aircraft. The procedure essentially consists of exploiting the aerodynamic sweep exhibited by a 'shock surface' developed by a spanwise series of normal passage shocks. (Author)
A computer program is discussed which calculates and plots the flat plane projection of a printed circuit type strain gage lead which is to be attached to an axial compressor rotor or stator blade. The input required includes lead path descriptive coordinates and blade descriptive coordinates. (Author)
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